Systems and methods for assembling containerized aircraft

ABSTRACT

Methods and systems for assembling containerized aircraft as complete aircraft. The methods comprise removing aircraft components from shipping container(s), unloading the aircraft components from shipping fixture(s), removing tooling comprising aircraft component positioning structure(s) from the shipping container(s), loading aircraft component(s) onto aircraft component positioning structure(s), positioning the aircraft components in aircraft component installation positions, positioning the aircraft component(s) using the aircraft component positioning structure(s), and attaching the aircraft components to assemble the complete aircraft. The systems comprise aircraft components configured to be loaded into shipping container(s) in a shipping arrangement, unloaded from the shipping arrangement and attached to at least one other aircraft component to assemble the complete aircraft; shipping fixture(s) configured to support the aircraft components in the shipping arrangement, and tooling configured to facilitate assembly of the aircraft components and comprising aircraft component positioning structure(s) configured to position aircraft component(s) in aircraft component installation position(s).

FIELD

The present disclosure relates to systems and methods for assemblingcontainerized aircraft.

BACKGROUND

Traditionally, assembly of aircraft is performed in large, centralizedindoor assembly facilities, which rely on significant personnel, openfloor space, and extensive manufacturing infrastructure for assemblingaircraft. For example, conventional aircraft assembly facilitiestypically utilize production lines in conjunction with monument styletooling such as high bays and cranes for traditional assembly ofcritical aircraft components. The manufacturing requirements associatedwith traditional indoor assembly facilities not only are costly, but thecentralized nature of this type of manufacturing can create lengthy leadtimes resulting from production backup. Moreover, most complete aircraftmanufactured in these facilities must be certified and flight worthybefore being delivered to a customer, and the routes for deliveringsmaller aircraft typically are indirect and expensive. Thus, thereexists a need for systems and methods for assembling aircraft offsitefrom centralized, indoor assembly facilities that permit the assembly tobe performed in a variety of assembly environments, such as the locationof the receiving customer.

SUMMARY

Methods and systems for assembling containerized aircraft as completeaircraft are disclosed herein. The methods for assembling containerizedaircraft as complete aircraft comprise removing a plurality of aircraftcomponents supported on one or more shipping fixtures from one or moreshipping containers, unloading the plurality of aircraft components fromthe one or more shipping fixtures, and removing tooling from the one ormore shipping containers, in which the tooling comprises one or moreaircraft component positioning structures. The methods further compriseloading one or more aircraft components onto respective aircraftcomponent positioning structures, positioning the plurality of aircraftcomponents in corresponding aircraft component installation positions,in which the positioning of the one or more aircraft componentscomprises positioning using the respective aircraft componentpositioning structures, and assembling the plurality of aircraftcomponents as the complete aircraft by attaching each aircraft componentto at least one other aircraft component in the corresponding aircraftcomponent installation position.

The systems for assembling the containerized aircraft as the completeaircraft comprise a plurality of aircraft components configured to beloaded into one or more shipping containers in a shipping arrangement,in which each aircraft component of the plurality of aircraft componentsis configured to be unloaded from the shipping arrangement and attachedto at least one other aircraft component of the plurality of aircraftcomponents to assemble the plurality of aircraft components into thecomplete aircraft. The systems further comprise one or more shippingfixtures configured to support the plurality of aircraft components inthe shipping arrangement, and tooling configured to facilitate assemblyof the plurality of aircraft components into the complete aircraft, inwhich the tooling comprises one or more aircraft component positioningstructures that each are configured to position at least one respectiveaircraft component in a corresponding aircraft component installationposition during assembly of the complete aircraft.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a perspective view illustrating examples of an aircraft formedutilizing the systems and/or methods for assembling a containerizedaircraft as a complete aircraft, according to the present disclosure.

FIG. 2 is a schematic representation depicting examples of systems forassembling a containerized aircraft as a complete aircraft, according tothe present disclosure.

FIG. 3 is a flowchart depicting methods of systems for assembling acontainerized aircraft as a complete aircraft, according to the presentdisclosure.

FIG. 4 is a somewhat less schematic illustration depicting an example oftooling and aircraft components in a shipping arrangement.

FIG. 5 illustrates specific examples of removing aircraft components andtooling from shipping containers.

FIG. 6 illustrates a specific example of the tooling and the aircraftcomponents in the shipping arrangement.

FIG. 7 is an exploded view illustrating an example of a portion of theaircraft components in the shipping arrangement.

FIG. 8 illustrates a specific example of features of a wing shippingfixture and portions of systems that may be utilized in unloading.

FIG. 9 illustrates a specific example of features of a wing shippingfixture and portions of systems that may be utilized in unloading.

FIG. 10 illustrates an example of wing positioning structures indexed tothe fuselage positioning structure.

FIG. 11 illustrates an example of an empennage positioning structureduring the indexing.

FIG. 12 illustrates an example of loading a wing onto a wing positioningstructure.

FIG. 13 illustrates an example of loading a vertical tailfin assemblyonto the empennage positioning structure.

FIG. 14 illustrates an example of loading an engine assembly onto anengine positioning structure.

FIG. 15 illustrates an example of positioning wings utilizing wingpositioning structures.

FIG. 16 illustrates a specific example of the empennage positioningstructure.

FIG. 17 illustrates a specific example of a vertical tailfin assemblyloaded onto the empennage positioning structure.

FIG. 18 illustrates a specific example of positioning a horizontalstabilizer assembly.

FIG. 19 illustrates a specific example of positioning an empennageassembly utilizing the empennage positioning structure.

FIG. 20 illustrates a specific example of positioning a nose assembly.

FIG. 21 illustrates a specific example of positioning an engine assemblyutilizing an engine positioning structure.

FIG. 22 illustrates examples of component parts of systems that may beutilized during assembling and disengaging.

FIG. 23 illustrates a specific example of assembling aircraft fairings,rudders, and flaps.

FIG. 24 illustrates a specific example of portions of systems that maybe utilized during assembling a landing gear assembly.

FIG. 25 illustrates a specific example of portions of systems that maybe utilized during assembling the landing gear assembly.

DETAILED DESCRIPTION

Systems and methods for the assembly of a containerized aircraft as acomplete aircraft are disclosed herein. Generally, in the Figures,elements that are likely to be included in a given example areillustrated in solid lines, while elements that are optional to a givenexample are illustrated in broken lines. However, elements that areillustrated in solid lines are not essential to all examples of thepresent disclosure, and an element shown in solid lines may be omittedfrom a particular example without departing from the scope of thepresent disclosure.

FIG. 1 illustrates an example of a complete aircraft that may beconstructed according the methods disclosed herein and/or utilizing thesystems disclosed herein. FIG. 2 provides a schematic representation ofexamples of systems 200 for assembling a containerized aircraft as acomplete aircraft, FIG. 3 provides a flowchart schematicallyrepresenting methods 100 for assembling the containerized aircraft asthe complete aircraft, and FIGS. 4-25 provide somewhat less schematicbut still illustrative examples of component parts of systems 200, suchas that perform and/or are utilized in connection with the performanceof one or more steps of methods 100, and/or structures comprisingcomponent parts of systems 200 that are constructed with the performanceof one or more steps of methods 100. Elements that serve a similar, orat least substantially similar, purpose are labelled with like numbersin each of FIGS. 1-25, and these elements may not be discussed in detailherein with reference to each of FIGS. 1-25. Similarly, all elements maynot be labelled in each of FIGS. 1-25, but reference numerals associatedtherewith may be utilized herein for consistency. Elements, components,and/or features that are discussed herein with reference to one or moreof FIGS. 1-25 may be included in and/or utilized with any of FIGS. 1-25without departing from the scope of the present disclosure.

Methods 100 are not required to have the schematically represented stepsof FIG. 3 performed in the illustrated order. The methods and stepsillustrated in FIG. 3 are not limiting and other methods and steps arewithin the scope of the present disclosure, including methods havinggreater than or fewer than the number of steps illustrated, asunderstood from the discussions herein.

FIG. 1 illustrates an example of a complete aircraft 800 that may beconstructed according to methods 100 and/or utilizing systems 200. WhileFIG. 1 illustrates complete aircraft 800 in the form of a fixed wingaircraft, other types and configurations of complete aircraft 800 arewithin the scope of the present disclosure, including, but not limitedto, helicopters. Complete aircraft 800 may comprise a fuselage assembly310, which generally corresponds to the main body of complete aircraft800, one or more wings 320, and an empennage assembly 330. As shown, insome examples, empennage assembly 330 includes a vertical tailfinassembly 332 and a horizontal stabilizer assembly 334. Complete aircraftfurther may comprise a nose assembly 350, one or more engine assemblies340, one or more flaps 380, one or more rudders 382, and a plurality ofaircraft fairings 370. As discussed herein, complete aircraft 800further may comprise additional and/or alternative components and/orassemblies that are not explicitly illustrated in FIG. 1. For example,fuselage assembly 310 may comprise seats for carrying passengers,stowage compartments, one or more restrooms, and/or a galley, dependingon the function of the complete aircraft. As another example, noseassembly 350 may comprise a cockpit having control systems and seatingfor one or more pilots.

With initial reference to the examples of FIG. 2, systems 200 forassembling the containerized aircraft as the complete aircraft comprisea plurality of aircraft components 300 that are configured to be loadedinto one or more shipping containers 210 in a shipping arrangement 220,and one or more shipping fixtures 230 that are configured to support theplurality of aircraft components 300 in the shipping arrangement 220.Each aircraft component 300 is configured to be unloaded from theshipping arrangement 220 and attached to at least one other aircraftcomponent 300 to assemble the plurality of aircraft components 300 asthe complete aircraft 800. Systems 200 further comprise tooling 400configured to facilitate assembly of the plurality of aircraftcomponents 300 as the complete aircraft 800. Tooling 400 is configuredto be loaded into and unloaded from the shipping container(s) 210 andcomprises one or more aircraft component positioning structures 410.Each aircraft component positioning structure 410 is configured toposition at least one respective aircraft component 300 in at least onecorresponding aircraft component installation position during assemblyof the complete aircraft. Further illustrated in FIG. 2, systems 200optionally comprise shipping container(s) 210 and a conveying mechanism500 for conveying tooling 400, shipping fixtures 230, aircraftcomponents 300, and/or combinations thereof during assembly of thecomplete aircraft.

In some examples, systems 200 comprise a single set of tooling 400 andmore than one set of aircraft components 300, to permit more than onecomplete aircraft 800 to be assembled at a particular assembly locationusing the single set of tooling 400. As examples, systems 200 maycomprise one set of tooling 400 and at least two sets, at least threesets, at least four sets, at least five sets, at least ten sets, and/orat least twenty sets of aircraft components 300.

As referred to herein, the containerized aircraft also may be describedas a modular aircraft, a unitized aircraft, a kitted aircraft, and aconstructible aircraft. Plurality of aircraft components 300 also may bedescribed as a plurality of interconnectable assemblies, in which eachinterconnectable assembly is configured to be attached to, connected to,or joined with at least one other interconnectable assembly to comprisea portion of the complete aircraft. For example, as discussed herein,one or more aircraft components 300 may comprise a plurality ofpreassembled subcomponents that collectively form a completeinterconnectable assembly. FIG. 2 schematically illustrates examples ofaircraft components 300 such as a fuselage assembly 310, one or morewings 320, a horizontal stabilizer assembly 334, a vertical tailfinassembly 332, one or more engine assemblies 340, and a landing gearassembly 360. In some examples, plurality of aircraft components 300further comprises one or more wing struts 326, a plurality of aircraftfairings 370, one or more flaps 380, one or more rudders 382, one ormore propellers 342, and/or a nose assembly 350. While FIG. 2illustrates each specific aircraft component 300 as being an individual,or a discrete assembly, it is within the scope of the present disclosethat any subset of aircraft components 300 illustrated in FIG. 2 may bepreassembled prior to assembly of the containerized aircraft. Forexample, nose assembly 350 may be preassembled with fuselage assembly310. Likewise, wing(s) 320 may be preassembled with flap(s) 380, andengine assembly(s) 340 may be preassembled with propeller(s) 342.

With continued reference to FIG. 2, in some examples, at least some ofthe aircraft components 300 comprise at least one predrilledinstallation interface 390, in which each predrilled installationinterface 390 is configured to be selectively joined with at least oneother predrilled installation interface 390 to permit drilling-freeattachment of two or more respective aircraft component(s) 300. In suchexamples, predrilled installation interfaces 390 may enhance theprecision with which the two or more respective aircraft components 300are attached and/or reduce the tooling required for assembling aircraftcomponents 300.

In some examples, at least a subset of aircraft components 300 compriseinterconnectable preinstalled portions of one or more aircraft systems394, in which the interconnectable preinstalled portions of eachaircraft system 394 are configured to be interconnected to form acomplete aircraft system. The interconnectable preinstalled portions ofeach aircraft system 394 are configured to be interconnected duringassembly of the aircraft by any suitable mechanism. In some examples,preinstalled portions of a given aircraft system 394 comprise one ormore quick connects that are configured to interconnect with one or morequick connects comprised in one or more other preinstalled portions ofthe given aircraft system 394. In such examples, the quick connects mayfacilitate facile and precision assembly of a given complete aircraftsystem. Examples of complete aircraft systems include electronicsystems, hydraulic systems, mechanical systems, hydro-mechanicalsystems, electromechanical systems, fuel systems, and/or combinationsthereof. In such examples, each complete aircraft system is configuredto facilitate one or more aspects of aircraft control and/or aircraftoperation, with illustrative, non-exclusive examples including flapcontrol, rudder control, elevator control, communications control,engine control, and fuel supply. For example, when the plurality ofaircraft components 300 comprises one or more wings 320 and one or moreflaps 380, wing(s) 320 and flap(s) 380 may comprise interconnectablepreinstalled portions of a mechanical system that are interconnected toform a complete mechanical system for actuating, or controlling flap(s)380. In some examples, one or more aircraft components 300 and/orinterconnectable preinstalled portions of aircraft system(s) 394 arepretested and/or pre-certified, such that aircraft component testingand/or certification is not required during assembly of the plurality ofaircraft components 300.

As further shown in FIG. 2, in some examples one or more aircraftcomponents 300 comprise one or more handling fittings 392 that areconfigured to releasably engage with conveying mechanism 500 and/or aconveying mechanism handle(s) 480 to facilitate removing, unloading,loading, and/or positioning of the respective aircraft component 300.Handling fitting(s) 392 comprise any suitable structure for releasablyengaging an aircraft component 300 with conveying mechanism 500 orconveying mechanism handle(s) 480, such as a D-ring, a closed loop, ahook, a slot, and/or a lip.

FIG. 2 further illustrates specific examples of shipping fixture(s) 230comprising systems 200. As defined herein, shipping fixture(s) 230comprises any suitable structure for supporting aircraft components 300and/or tooling 400 in shipping arrangement 220. In some examples,shipping fixture(s) 230 comprise one or more discrete structures, inwhich each shipping fixture 230 is configured to support at least aportion of aircraft component(s) 300 and/or a portion of tooling 400.Additionally or alternatively, in some examples, shipping fixture(s) 230comprise shipping container(s) 210. In such examples, one or moreaircraft components 300 and/or tooling 400 are directly supported byshipping container(s) 210 in shipping arrangement 220. As shown,examples of shipping fixture(s) 230 comprise one or more of a fuselageshipping fixture 240, a wing shipping fixture 250, an empennage shippingfixture 260, and an engine shipping fixture 270. While the examplesschematically represented in FIG. 2 indicate each of the above specificshipping fixtures 230 as being configured to support a single orspecific aircraft component 300, in many examples, at least one shippingfixture 230 is configured to simultaneously support at least two, atleast three, at least four, at least five, and/or at least ten aircraftcomponents 300 in shipping arrangement 220.

Shipping container(s) 210 may be described as standard shippingcontainer(s) 210, or intermodal container(s) 210 that configured forthat are configured for transport via one or more of rail, truck, ship,and/or plane. Shipping container(s) 210 may include any suitabledimensions for containerizing systems 200. Examples of suitabledimensions of shipping container 210 include an external height of 2meters, 2.6 meters, or 2.9 meters, an external width of 2 meters, 2.4meters, or 2.6 meters, and/or an external length of 6.1 meters, 12.2meters, 13.7 meters, 14.6 meters, or 16.2 meters.

With continued reference to the examples of FIG. 2, systems 200 furthercomprise tooling 400 that is configured to facilitate assembly of theplurality of aircraft components 300 as the complete aircraft 800. Insome examples, tooling 400 is configured to be manually operated, suchthat assembly of the complete aircraft 800 may be performed with tooling400 independently of computer aided systems. In some examples, tooling400 is configured to facilitate assembly of the complete aircraft in aplurality of assembly environments, in which each assembly environmentcomprises one or more assembly surfaces. Stated another way, tooling 400may be described as being adaptable to facilitate assembly of thecomplete aircraft in a wide array of assembly environments and/or on awide array of assembly surfaces. Examples of assembly environmentsinclude one or more of an indoor assembly environment, an outdoorassembly environment, an airfield, and/or an unsupported assemblyenvironment. As defined herein, unsupported assembly environment refersto any assembly environment in which traditional assembly fixtures, suchas overhead cranes and permanent lifts, are not necessarily available.Examples of assembly surfaces include one or more of an uneven assemblysurface, a concrete assembly surface, a dirt assembly surface, a grassyassembly surface, an unfinished assembly surface, and/or a wet assemblysurface.

As schematically represented in FIG. 2, tooling 400 comprises one ormore aircraft component positioning structures 410. Aircraft componentpositioning structure(s) 410 also may be referred to herein aspositioning structure(s), supporting structure(s), positioningfixture(s), aircraft component positioning fixture(s), aircraftcomponent support frame(s), and/or aircraft component orientingfixture(s). Stated in slightly different terms, each aircraft componentpositioning structure 410 is configured to support and position one ormore respective aircraft components 300 during assembly of the completeaircraft. Examples of aircraft component positioning structure(s) 410include one or more of a fuselage positioning structure 420, one or morewing positioning structures 430, an empennage positioning structure 440,and/or one or more engine positioning structures 450. While the aboveexamples indicate each aircraft component positioning structures 410 asbeing configured to position a particular aircraft component 300, insome examples, one or more aircraft component positioning structures410, or portions thereof, are configured to position more than oneaircraft component 300. As discussed in more detail herein with respectto methods 100, in some examples, empennage positioning structure 440 isconfigured to position vertical tailfin assembly 332, horizontalstabilizer assembly 334, and empennage assembly 330. As another example,jack mechanism(s) 460 comprising engine positioning structure(s) 450also may be utilized in positioning fuselage assembly 310. Additionallyor alternatively, one or more shipping fixtures 230 are utilized asaircraft component positioning structure(s) 410 and/or portions ofaircraft component positioning structure(s) 410. As further illustratedin FIG. 2, in some examples, tooling 400 further comprises one or morestabilization jacks 490 configured to stabilize one or more aircraftcomponents 300, such as, when aircraft component(s) 300 are not beingsupported by a respective aircraft component positioning structure 410.

Each aircraft component positioning structure 410 is configured toposition at least one respective aircraft component 300 in thecorresponding aircraft component installation position during assemblyof the aircraft. In some examples, in order to adequately positionaircraft component 300 in the corresponding installation position, it isdesirable to perform positional adjustments on aircraft component 300utilizing the respective aircraft component positioning structure 410.With this in mind, in some examples, one or more aircraft componentposition structures 410 comprise one or more jack mechanisms 460 and/orone or more drive mechanisms 470 that are configured to facilitate thepositional adjustments. In some such examples, jack mechanism(s) 460and/or drive mechanism(s) 470 that comprise a particular aircraftcomponent positioning structure 410 are configured to be disengaged fromthe particular aircraft component positioning structure 410 and utilizedin a different aircraft component positioning structure 410.

In some examples, systems 200 further comprise a plurality of fasteners402 that are utilized to attach aircraft components 300. Additionally oralternatively, tooling 400 comprises a plurality of fastening mechanisms404 configured to facilitate attachment of aircraft components 300,optionally with fasteners 402. As discussed herein, fasteners 402 aredefined as any suitable structure and/or combination of structures thatadequately attach two or more aircraft components 300. In some examples,one or more aircraft components 300 comprise one or more fasteners 402and/or portions of fasteners 402. Fasteners 402 that are utilized toattach any set of aircraft components 300 may be the same as ordifferent from fasteners 402 that are utilized to attach a different setof aircraft components 300. Fastening mechanisms 404 are defined hereinas any suitable mechanism for attaching two or more aircraft components300 and may be utilized in connection with fasteners 402 orindependently of fasteners 402. Examples of fastening mechanisms 404include hand tools, pneumatically driven hand tools, wrenches, drivers,welding machinery, riveters, swaggers, clamps, presses, pliers, vices,and/or crimpers.

As schematically represented in FIG. 2, in some examples, systems 200further comprises a conveying mechanism 500 that is configured to conveya plurality of aircraft components 300, shipping fixture(s) 230,shipping container(s) 210, and/or tooling 400 during assembly of thecomplete aircraft 800. In some examples, conveying mechanism 500 isconfigured to unload one or more aircraft components 300 from one ormore respective shipping fixtures 230. Additionally or alternatively,conveying mechanism 500 may be configured to unload shipping fixture(s)230 and/or tooling 400 from shipping container(s) 210. As yet moreexamples, conveying mechanism 500 may be configured to load one or moreaircraft components 300 onto one or more respective aircraft componentpositioning structure(s) 410, and/or position one or more aircraftcomponents 300 during assembly of the complete aircraft. As discussed inmore detail herein with respect to methods 100, in some examples,conveying mechanism 500 comprises a forklift 510 or any otheruser-operated machinery configured to facilitate removing, unloading,loading, and/or positioning of component parts of systems 200. For anyexample in which tooling 400 comprises conveying mechanism 500, tooling400 further may comprise one or more conveying mechanism handles 480that each are configured associate with conveying mechanism 500 andreleasably engage with one or more respective handling fittings 392comprised in one or more aircraft components 300, one or more shippingfixtures 230, and/or one or more aircraft component positioningstructures 410. Conveying mechanism handle(s) 480 comprise any suitablestructure for releasably engaging handling fitting(s) 392 such as one ormore of a hook, a loop, a chain, a strap, a boom, a latch, a clamp,and/or a slot receiver. Alternatively, shipping fixture(s) 230, tooling400, and/or aircraft components 300 may be configured to releasablyengage with conveying mechanism 500 without requiring handling fittings392 and/or conveying mechanism handles 480. Stated in slightly differentterms, in some examples, shipping fixture(s) 230, tooling 400, and/oraircraft components 300 are configured to releasably engage with anygeneric conveying mechanism that may be provided at an assembly locationsuch as to perform any steps of methods 100 that utilize conveyingmechanism 500. It also is within the scope of the present disclosurethat conveying mechanism 500 may comprise a plurality of conveyingmechanisms 500, such as a plurality of forklifts 510.

Turning now to the examples schematically represented in FIG. 3, butwith continued reference to FIG. 2, methods 100 for assembling theplurality of aircraft components as the complete aircraft compriseremoving the plurality of aircraft components and the tooling from theshipping containers at 120, unloading the plurality of aircraftcomponents from one or more shipping fixtures at 130, and loading one ormore aircraft components onto one or more respective aircraft componentpositioning structures at 140. Methods 100 further comprise positioningthe plurality of aircraft components in the corresponding aircraftcomponent installation positions at 150, which comprises positioning theone or more aircraft components in the corresponding aircraft componentinstallation positions using the one or more respective aircraftcomponent positioning structures at 152. Methods 100 yet furthercomprise assembling the plurality of aircraft components in thecorresponding aircraft component installation positions at 160, whichcomprises attaching each aircraft component to at least one otheraircraft component at 162.

To more clearly illustrate the steps of methods 100 that areschematically represented in FIG. 3, the following discussion makesreference to the specific examples illustrated in FIGS. 4-25. While manyof the examples of FIGS. 4-25 illustrate specific component parts ofsystems 200 and/or structures comprising specific component parts ofsystems 200 that are utilized and/or constructed in connection withperforming one or more steps of methods 100, the one or more stepsrepresented in each of FIGS. 4-25 may be performed in connection withone or more different component parts of systems 200 without departingfrom the scope of the present disclosure. Additionally, while methods100 comprise steps that are schematically represented in FIG. 3 as beingperformed in connection with more than one aircraft component, methods100 do not require any given step be performed in connection with morethan one aircraft component simultaneously, and more than one step ofmethods 100 may be performed in connection with an individual aircraftcomponent independently of any other aircraft component. For example,while FIG. 3 indicates removing the aircraft components from theshipping container(s) at 120, and unloading the aircraft components fromthe shipping fixture(s) at 130, methods 100 may include removing and/orunloading one or more aircraft components before or after all otheraircraft components are removed and/or unloaded from the shippingcontainer(s).

As shown in FIG. 3, in some examples, methods 100 comprise preassemblingthe aircraft components and the tooling at 80. The preassembling at 80may be performed prior to any other step of methods 100. In someexamples, the preassembling at 80 comprises preassembling one or moresubcomponents that define a given aircraft component 300 of systems 200.The preassembling at 80 also may comprise installing preinstalledportions of aircraft systems 394 in two or more aircraft components 300.Additionally or alternatively, the preassembling at 80 comprises formingpredrilled installation interfaces 390 in two or more aircraftcomponents 300. As yet more examples, the preassembling at 80 furthermay comprise preassembling one or more aircraft component positioningstructures 410. In some examples, the preassembling at 80 is performedat a single pre-fabrication location, and in other examples thepreassembling at 80 is performed at multiple pre-fabrication locations.

Referring again to FIG. 3, methods 100 also may comprise loading thetooling and the aircraft components at 90. The loading at 90 may beperformed prior to the delivering at 110 and/or subsequent to thepreassembling at 80. In some examples, the loading at 90 comprisesloading aircraft components 300 onto shipping fixture(s) 230 in shippingarrangement 220. In some examples, the loading at 90 comprises loadingtooling 400 onto shipping fixture(s) 230 in shipping arrangement 220.The loading at 90 further may comprise loading aircraft components 300and tooling 400 into shipping container(s) 210. In some examples, theloading at 90 is performed at a pre-fabrication location where aircraftcomponents 300 and/or tooling are preassembled. Additionally oralternatively, the loading at 90 may be performed at a deliverylocation, which may be the same as or different from the pre-fabricationlocation. As a more specific example, for examples in which thepreassembling at 80 is performed at multiple pre-fabrication locations,the delivery location may correspond to one of the pre-fabricationlocations and/or may be separate from any of the pre-fabricationlocations. In some examples, the loading at 90 is performed by the sameparty that performs the preassembling at 80.

As shown in FIG. 3, methods 100 optionally comprise delivering thetooling and aircraft components in the one or more shipping containersat 110. The delivering at 110 may be performed subsequent to thepreassembling at 80, subsequent to the loading at 90, and/or prior toany other step of methods 100. In some examples, the delivering at 110comprises shipping, or delivering, the one or more shipping containersfrom the pre-fabrication location, in which one or more of the aircraftcomponents are formed and/or preassembled, to the assembly location.Additionally or alternatively, the delivering at 110 comprisesdelivering the one or more shipping containers to the delivery location.In any such examples, the delivering at 110 additionally oralternatively comprises delivering systems 200 to a location of acustomer. In some examples, shipping containers 210 are owned by thesame party that performs the preassembling at 80 and/or the loading at90. Alternatively, shipping containers 210 are owned by a third party,such as a freight or shipping company.

As discussed in more detail herein, the delivering at 110 comprisesdelivering the tooling and the aircraft components in the shippingarrangement and any suitable number of shipping containers may beutilized to house and/or support the tooling and the aircraft componentsin the shipping arrangement. For some examples in which systems 200comprise conveying mechanism 500, conveying mechanism 500 is providedand/or available at the assembly location. Thus, in such examples, thedelivering at 110 does not comprise delivering conveying mechanism 500.Having conveying mechanism 500 at the assembly location may be desirableto reduce weight and/or space requirements for the delivering at 110.Moreover, a customer of a system 200 may readily have available one ormore suitable conveying mechanisms 500. For other examples in whichsystems 200 comprise conveying mechanism 500, conveying mechanism 500 isdelivered along with tooling 400 and aircraft components 300 in shippingcontainers 210.

In some examples, one or more of steps 110-195 of methods 100 areperformed by and/or overseen by one or more authorized personnel at theassembly location. Thus, in some examples, the delivering at 110comprises sending the one or more authorized personnel to the assemblylocation, which may be performed separately from delivering the toolingand the aircraft components. In some examples, the one or moreauthorized personnel are employed by the party that performs thepreassembling at 80, the loading at 90, and/or the delivering at 110,and/or that sells, leases, and/or otherwise delivers a system 200 to acustomer. Additionally or alternatively, the one or more authorizedpersonnel are trained by and/or authorized by the same party thatperforms the preassembling at 80, the loading at 90, and/or thedelivering at 110 to assemble the complete aircraft, and/or that sells,leases, and/or otherwise delivers a system 200 to a customer.

Turning to FIG. 4, illustrated is an example of tooling 400 andplurality of aircraft components 300 loaded into shipping container(s)210 in shipping arrangement 220. While FIG. 4 illustrates an example inwhich aircraft components and tooling 400 are loaded into three shippingcontainers 210, it is within the scope of the present disclosure thattooling 400 and aircraft components 300 may be configured to be loadedinto and unloaded from any suitable number of shipping containers 210,with examples including at most 1 shipping container, at most 2 shippingcontainers, at most 4 shipping containers, at most 5 shippingcontainers, at most 10 shipping containers, at least 10 shippingcontainers, at least 15 shipping containers, and/or at least 20 shippingcontainers.

Referring back to the examples schematically represented in FIG. 3,methods 100 comprise removing the aircraft components and the toolingfrom the shipping containers at 120. In some examples, the removing at120 comprises engaging one or more shipping fixtures with the conveyingmechanism at 122 and conveying the one or more shipping fixtures fromthe one or more shipping containers at 124 to remove at least a portionof the plurality of aircraft components and/or at least a portion of thetooling from the one or more shipping containers.

FIG. 5 illustrates less schematic, yet still illustrative, examples ofthe removing at 120. In the examples illustrated in FIG. 5, conveyingmechanism 500 comprises three forklifts 510 and each shipping fixture230 supports a portion of the plurality of aircraft components 300.While FIG. 5 illustrates examples in which three separate forklifts 510are utilized to convey three separate shipping fixtures 230 from threeshipping containers 210, as discussed herein, it within the scope of thepresent disclosure that systems 200 may include a single forklift 510,and each shipping fixture 230 is conveyed from a shipping container 210utilizing a single forklift 510. As shown in FIG. 5, the engaging at 122comprises engaging each shipping fixture 230 with a forklift 510, andthe removing 120 comprising conveying 124 each shipping fixture 230 witha forklift 510 from a shipping container 210 to remove the portion ofaircraft components 300 that are supported on the shipping fixture 230from the shipping container 210. Further shown in the examples of FIG.5, shipping fixtures 230 optionally comprise handling fitting(s) 392that are configured to engage with conveying mechanism 500 and/orconveying mechanism handle 480 during the removing at 120.

FIG. 6 provides an illustrative example of the plurality of aircraftcomponents 300 and tooling 400 in shipping arrangement 220 prior toand/or following the removing at 120. As shown, shipping fixtures 230are configured to support aircraft components 300 and tooling 400 inshipping arrangement 220, in which aircraft components 300 and tooling400 are arranged to be loaded into, unloaded from, and/or transported inshipping container(s) 210. In the specific example illustrated in FIG.6, shipping arrangement 220 comprises a plurality of aircraft components300 supported on two shipping fixtures 230 and at least a portion oftooling 400 is supported on a third shipping fixture 230. Morespecifically, in the example shown, a fuselage shipping fixture 240supports fuselage assembly 310, and a wing shipping fixture 250 supportswing(s) 320. Further illustrated in FIG. 6, in some examples, fuselageassembly 310 comprises an open internal volume 318, and one or moreaircraft components 300 are received within open internal volume 318 inshipping arrangement 220.

While FIG. 6 illustrates an example of shipping arrangement 220 in whichplurality of aircraft components 300 are supported on at least twoshipping fixtures 230 and tooling 400 is supported on a third shippingfixture 230, it is within the scope of the present disclosure thatsystems 200 comprise any suitable number of shipping fixtures 230, andaircraft components 300 and tooling 400 may be supported by shippingfixture(s) 230 in any suitable set of combinations and/or divisions inshipping arrangement 220. For example, in some examples, systems 200comprise a single shipping fixture 230 that supports both tooling 400and the plurality of aircraft components 300. Alternatively, systems 200may comprise at least 2, at least 4, at least 8, at least 10, at least20, at most 2, at most 3, at most 4, at most 5, at most 8, at most 10,and/or at most 20 shipping fixtures 230 for supporting plurality ofaircraft components 300 and/or tooling 400 in the shipping arrangement.

FIGS. 7-9 provide more detailed examples of portions of shippingarrangement 220. FIG. 8 illustrates an example of aircraft components300 that may supported on wing shipping fixture 250. As shown in thisexample, in addition to wing(s) 320, in some examples, wing shippingfixture 250 is configured to support vertical tailfin assembly 332, noseassembly 350, at least a portion of aircraft fairings 370, andpropellers 342. Now referring to the exploded view illustrated in FIG.7, in some examples, engine assembly(s) 340 and a portion of theplurality of aircraft fairings 370 are supported on an engine shippingfixture 270, and horizontal stabilizer assembly 334, at least a portionof aircraft fairings 370, and flap(s) 380 are supported on empennageshipping fixture 260. As shown in this example, empennage shippingfixture 260 and engine shipping fixture 270, together with therespectively supported aircraft components 300, are configured to bereceived within open internal volume 318 of fuselage assembly 310.

Turning back to the examples schematically represented in FIG. 3,methods 100 further comprise unloading the plurality of aircraftcomponents from the one or more shipping fixtures at 130. The unloadingis performed in any suitable manner such that each aircraft component isadequately unloaded from the one or more shipping fixtures. Theunloading at 130 may be performed subsequent to the removing at 120,substantially simultaneously with the removing at 120, prior to theloading at 140, and/or prior to the positioning at 150. As an example,the unloading at 130 may be performed substantially simultaneously withthe removing at 120 for examples in which the shipping arrangementcomprises one or more aircraft components directly supported by one ormore shipping containers. Additionally or alternatively, the unloadingat 130 may be performed subsequent to the removing at 120 for examplesin which the shipping arrangement comprises one or more aircraftcomponents supported by a shipping fixture that comprises a discretesupport structure.

With continued reference to FIG. 3, in some examples, the unloading at130 comprises lifting one or more aircraft components from one or morerespective shipping fixtures at 132. In some such examples, the liftingis performed with the conveying mechanism at 134. FIGS. 8-9 provide morespecific illustrative examples of the unloading at 130, the lifting at132, 134 and component parts of systems 200 utilized and/or unloaded inconnection with these steps. More specifically, FIG. 8 illustratesexamples of features of wing shipping fixture 250, wings 320, conveyingmechanism 500, and conveying mechanism handle(s) 480 that may beutilized during the unloading at 130, the lifting at 132, and/or thelifting at 134. In the examples shown, wing shipping fixture 250comprises one or more hinged wing support members 252, in which eachhinged wing support member 252 is configured to operatively support awing 320 and pivot between a shipping orientation 282 and an unloadingorientation 284. In the specific examples illustrated in FIG. 8, wingshipping fixture 250 comprises a first hinged wing support member 254positioned in the shipping orientation 282 and a second hinged supportmember 256 positioned in unloading orientation 284. In shippingorientation 282, hinged wing support member 252 is configured to supportwing 320 with a chord 322 of wing 320 oriented upwardly (i.e., generallyvertically). In unloading orientation 284, hinged wing support member252 is configured to support wing 320 with chord 322 of wing 320oriented outwardly (i.e., generally horizontally). Further illustratedin the examples of FIG. 8, wings 320 comprise one or more handlingfittings 392 that are configured to engage with one or more respectiveconveying mechanism handles 480 associated with conveying mechanism 500.In some of the examples represented in FIG. 8, conveying mechanism 500comprises forklift 510, and conveying mechanism handle(s) 480 comprisesforklift boom handle(s) 482. Thus, in the examples shown, unloading 130wing(s) 320 comprises pivoting hinged wing support member(s) 252 fromshipping orientation 282 to unloading orientation 284, releasablyengaging handling fitting(s) 392 with conveying mechanism handle(s) 480,which optionally comprises forklift boom handle(s) 482, and liftingwings 320 from wing shipping fixture with conveying mechanism 500, whichoptionally comprises forklift 510.

FIG. 9 illustrates specific examples of features of conveying mechanism500, conveying mechanism handle(s) 480, and vertical tailfin assembly332 that may be utilized during the unloading at 130, the lifting at132, and/or the lifting at 134. In the examples shown, vertical tailfinassembly 332 comprises one or more handling fittings 392 that areconfigured to engage with conveying mechanism handle(s) 480, andvertical tailfin assembly 332 is supported by wing shipping fixture 250such that handling fitting(s) 392 are accessible to conveying mechanism500. In some of the examples of FIG. 9, conveying mechanism 500comprises forklift 510, and conveying mechanism handle(s) 480, whichoptionally comprise forklift boom handle(s) 482, are associated withconveying mechanism 500. Thus, in such examples, unloading 130 verticaltailfin assembly 332 comprises engaging handling fitting(s) 392 ofvertical tailfin assembly 332 with conveying mechanism handle(s) 480,which optionally comprise forklift boom handle(s) 482, and liftingvertical tailfin assembly 332 from wing shipping fixture 250 withconveying mechanism 500, which optionally comprises forklift 510.

While FIGS. 8-9 illustrate specific examples of unloading 130 andlifting 132, 134 of wing(s) 320 and vertical tailfin assembly 332, it iswithin the scope of the present disclosure that similar steps may beperformed to unload other aircraft components 300.

Turning back to FIG. 3 and with continued reference to FIG. 2, in someexamples, methods 100 comprise indexing one or more aircraft componentpositioning structures to the fuselage positioning structure at 135. Theindexing at 135 is performed to facilitate proper placement of the oneor more aircraft component positioning structures during assembly of thecomplete aircraft. The indexing at 135 may be performed subsequent tothe removing at 120, subsequent to the unloading at 130, subsequent tothe loading at 140, prior to the loading at 140, and/or prior to thepositioning at 150. In some examples, the fuselage positioning assemblyand at least one other aircraft component positioning structure eachcomprise a base structure that is configured to support the aircraftcomponent positioning structure on the assembly surface. In some suchexamples, the indexing at 135 comprises engaging a portion of the basestructure of an aircraft component positioning structure and the basestructure of the fuselage positioning structure. In some such examples,the base structures of the fuselage positioning structure and theaircraft component positioning structure each comprise a laterallyextending track, and in such examples, the laterally extending tracksare engaged during the indexing at 135.

FIGS. 10-11 provide specific, illustrative examples of the indexing at135. With initial reference to FIG. 10, in some examples, the indexingat 135 comprises indexing one or more wing positioning structures 430 tofuselage positioning structure 420. As shown, each wing positioningstructure 430 comprises a base structure 412 having a laterallyextending track 416 that is configured to support wing positioningstructure 430 on an assembly surface 772, and fuselage positioningstructure 420 comprises a base structure 412 having a laterallyextending track 416 for supporting fuselage assembly 310 on the assemblysurface 772. In some such examples, the indexing at 135 comprisesengaging a portion of laterally extending track 416 of each wingpositioning structure 430 with laterally extending track 416 of fuselagepositioning structure 420, such as to secure wing positioningstructure(s) 430 in the proper positions. As shown, wing positioningstructure(s) 430 are indexed to fuselage positioning structure 420proximate to lateral sides 312 of fuselage assembly 310.

Now referring to FIG. 11, the indexing at 135 also may comprise indexingempennage positioning structure 440 to fuselage positioning structure420. As shown, empennage positioning structure comprises a basestructure 412 having a laterally extending track 416, and a portion of alaterally extending track 416 of empennage positioning structure 440 maybe engaged with a portion of laterally extending track 416 of fuselagepositioning structure 420. In the example shown, empennage positioningstructure 440 is indexed to fuselage positioning structure 420 proximateto an aft region 314 of fuselage assembly 310.

While FIGS. 10-11 illustrate the indexing at 135 as being performedwhile wing positioning structure(s) 430 and empennage positioningstructure 440 are not supporting aircraft components 300, it is withinthe scope of the present disclosure that the indexing at 135 may beperformed while any aircraft component positioning structure issupporting one or more respective aircraft components 300. Statedanother way, in some examples, the indexing at 135 is performedsubsequent to the loading at 140.

Referring back to the examples schematically represented in FIG. 3 andwith continued reference to FIG. 2, methods 100 further comprise loadingone or more aircraft components onto respective aircraft componentpositioning structures at 140. As indicated in FIG. 3, in some examples,the loading 140 further comprises loading the one or more aircraftcomponents with the conveying mechanism at 142. As discussed in moredetail herein, the loading at 140 may be performed subsequent to theunloading at 130, subsequent to the indexing at 135, prior to theindexing at 135, and/or prior to the positioning at 150.

FIGS. 12-14 provide specific, illustrative examples of the loading at140 and/or the loading at 142 and component parts of systems 200 thatmay be utilized and/or loaded during the loading at 140. With initialreference to FIG. 12, illustrated is an example in which the loading at140 comprises loading wing(s) 320 onto respective wing positioningstructure(s) 430. More specifically, in the example shown, wingpositioning structure(s) 430 are indexed to fuselage positioningstructure 420 prior to the loading the wing(s) at 140, and loading 140wing(s) 320 comprises loading 142 with conveying mechanism 500. In somesuch examples, wing(s) 320 comprise handling fitting(s) 392 that areconfigured to engage with conveying mechanism handle(s) 480 associatedwith conveying mechanism 500. In the specific example illustrated inFIG. 12, conveying mechanism comprises forklift 510, which is associatedwith forklift boom handle(s) 482.

Now referring to the examples represented in FIG. 13, the loading at 140also may comprise loading vertical tailfin assembly 332 onto empennagepositioning structure 440. As discussed in more detail herein withrespect to the unloading at 130, in some examples, loading 140, 142vertical tailfin assembly 332 comprises engaging handling fitting(s) 392of vertical tailfin assembly 332 with conveying mechanism handle(s) 480to load vertical tailfin assembly 332 onto empennage positioningstructure 440 with conveying mechanism 500. As further illustrated inFIG. 13, in some examples, the loading at 140 comprises loading 140aircraft component 300, such as vertical tailfin assembly 332, onto therespective aircraft component positioning structure 410 in a loadingorientation 442.

FIG. 14 provides another illustrative example of the loading at 140,142, in which engine assembly 340 is loaded onto engine positioningstructure 450. As shown, engine assembly 340 is supported by a portionof engine shipping fixture 270, and conveying mechanism 500 isconfigured to engage with engine shipping fixture 270 to load engineassembly 340 onto engine positioning structure 450. In some suchexamples, the loading 140, 142 comprises engaging and/or coupling enginepositioning structure 450 with engine shipping fixture 270. In some suchexamples, the portion of engine shipping fixture 270 is utilized inand/or defines a portion of engine positioning structure 450 duringsubsequent steps of methods 100.

Turning back to the examples of FIG. 3 and with continued reference toFIG. 2, methods 100 further comprise positioning each aircraft componentof the plurality of aircraft components in the corresponding aircraftcomponent installation position at 150. For the one or more aircraftcomponents that are loaded onto the one or more respective aircraftcomponent positioning structures, the positioning at 150 comprisespositioning using the respective aircraft component positioningstructures at 152. In some such examples, the positioning at 152 furthercomprises performing positional adjustments at 154 on one or moreaircraft components with the one or more respective aircraft componentpositioning structures. The positioning at 150 may be performedsubsequent to the unloading at 130, subsequent to the loading at 140,prior to the assembling at 160, substantially simultaneously with theassembling at 160, and/or subsequent to the assembling at 160.

As discussed herein, the corresponding aircraft component installationposition also may be referred to as the corresponding installationposition. The corresponding installation position of a particularaircraft component may be descried as a plotted or planned position ofthe particular aircraft component for the assembly of the containerizedaircraft. Stated in slightly different terms, the correspondinginstallation position may be described as a specific location that aparticular aircraft component is to be positioned relative to one ormore other aircraft components during assembly of the complete aircraft.More than one corresponding installation position may be assigned to asingle aircraft component depending on the order in which the aircraftcomponents are assembled. As discussed in more detail herein, in someexamples, the positioning at 150 is performed manually and/or withoutrequiring the use of positioning structure. In some such examples, thepositioning at 150 is performed with the conveying mechanism. For someexamples in which the positioning at 150 of a particular aircraftcomponent and/or pre-attached assembly of more than one aircraftcomponents is performed utilizing a respective aircraft componentpositioning structure at 152, the positioning at 152 is performed onmore than one aircraft component and/or pre-attached assembly ofaircraft components utilizing a single aircraft component positioningstructure.

In some examples, it is desirable to perform one or more positionaladjustments at 154 on one or more aircraft components and/or one or morepre-attached assemblies of aircraft components relative to thecorresponding installation position(s) utilizing the respective aircraftcomponent positioning structure. As examples, the one or more positionaladjustments may comprise one or more of a pitch adjustment, a rolladjustment, a yaw adjustment, an X positional adjustment, a Y positionaladjustment, and/or a Z positional adjustment. With this in mind, one ormore aircraft component positioning structures may be configured tofacilitate the one or more positional adjustments of one or morerespective aircraft components and/or one or more pre-attachedassemblies of aircraft components, such as the pitch adjustment, theroll adjustment, the yaw adjustment, the X positional adjustment, the Ypositional adjustment, and/or the Z positional adjustment. In some suchexamples, one or more aircraft component position structures compriseone or more jack mechanisms and/or one or more drive mechanisms that areconfigured to facilitate the positional adjustments. FIGS. 15-21 provideillustrative examples of aircraft components positioned during thepositioning at 150, 152, 154 as well as examples of elements of systems200 utilized during the positioning at 150, 152.

FIGS. 10 and 15 illustrate an example of features of wing positioningstructure(s) 430 that are utilized during positioning 150, 152, andadjusting 154 wing(s) 320. In the example shown, systems 200 comprisetwo wings 320 and two respective wing positioning structures 430, andthe wing positioning structure(s) 430 are indexed to fuselagepositioning structure 420 as described herein with respect to theindexing at 135. Each wing positioning structure 430 is configured tofacilitate one or more positional adjustments 700, comprising one ormore of a pitch adjustment 710, a yaw adjustment 720, a roll adjustment730, an X positional adjustment 740, a Y positional adjustment 750,and/or a Z positional adjustment 760 of wing 320 relative tocorresponding wing installation position 610. As shown, winginstallation position 610 generally is proximate to a lateral side 312of fuselage assembly 310. Each wing positioning structure 430 compriseslaterally extending track 416, and a vertical rise structure 414translationally coupled to laterally extending track 416 that isconfigured to operatively support wing(s) 320. Drive mechanism 470 thatis associated with vertical rise structure 414 is configured tofacilitate translational adjustments of vertical rise structure 414along laterally extending track 416, thereby permitting Y positionaladjustment 750 of wing 320. Wing positioning structure(s) 430 furthercomprises push mechanisms 472 positioned between vertical rise structure414 and laterally extending track 416 that are configured to facilitatelateral rotational or yaw adjustment of vertical rise structure 414relative to laterally extending track 416. In some examples, pushmechanisms 472 are configured to permit lateral adjustments of verticalrise structure 414 relative to laterally extending track 416. Stated indifferent terms, push mechanisms 472 permit wing positioning structure430 to facilitate yaw adjustment 720 and/or X positional adjustment 740of wing 320.

Perhaps best illustrated in the example of FIG. 15, wing positioningstructure(s) 430 comprise jack mechanisms 460 associated with verticalrise structure 414. Jack mechanisms 460 are configured to facilitate oneor more of pitch adjustment 710, roll adjustment 730, and/or Zpositional adjustment 760 of wing 320. Perhaps more clearly illustratedin FIG. 10, in some such examples, jack mechanisms 460 of wingpositioning structure(s) 430 comprise wing jack mechanisms 462, in whicheach wing jack mechanism 462 operatively contacts wing 320 at a contactpoint and is configured to translate vertically such as to facilitateand/or contribute to one or more of the pitch adjustment 710, rolladjustment 730, and/or Z positional adjustment 760 of wing 320. Thus,positioning wing(s) 320 at 150, 152 optionally comprises performing oneor more positional adjustment(s) 700 utilizing one or more features ofwing positioning structure(s) 430 at 154.

FIGS. 16-19 illustrate examples of the positioning at 150, 152, 154 withrespect to vertical tailfin assembly 332, horizontal stabilizer assembly334, and empennage assembly 330 utilizing empennage positioningstructure 440. FIG. 16 illustrates an example of empennage positioningstructure 440 prior to the loading at 140 and details features ofempennage positioning structure 440 that are configured to facilitateone or more of a pitch adjustment 710, a yaw adjustment 720, a rolladjustment 730, an X positional adjustment 740, a Y positionaladjustment 750, and/or a Z positional adjustment 760 of one or more ofvertical tailfin assembly 332, horizontal stabilizer assembly 334,and/or empennage assembly 330. More specifically, in this example,empennage positioning structure 440 comprises a laterally extendingtrack 416, and vertical rise structure 414 translationally coupled tolaterally extending track 416 that is configured to support therespective aircraft components. Drive mechanism 470 is associated withvertical rise structure 414 and is configured to facilitatetranslational adjustments of vertical rise structure 414 along laterallyextending track 416, and thus X positional adjustment 740 of the one ormore respective aircraft components. Empennage positioning structure 440further comprises push mechanisms 472 that are configured to facilitateyaw adjustment 720 and/or Y positional adjustment 750 of the one or morerespective aircraft components, such as by a similar mechanism to thatdiscussed with respect to wing positioning structure(s) 430. Jackmechanisms 460 associated with vertical rise structure 414 areconfigured to facilitate Z positional adjustment 760 and/or rolladjustment 730 of the respective aircraft component(s), and a rotatingdrive mechanism 474 associated with jack mechanism 460 are configured tooperatively contact the respective aircraft component(s) 300 andfacilitate pitch adjustment 710 of the respective aircraft component(s).Thus, positioning 150, 152 one or more of vertical tailfin assembly 332,horizontal stabilizer assembly 334, and empennage assembly 330optionally comprises performing any of the positional adjustment(s) 700utilizing empennage positioning structure 440 at 154.

For example, as discussed herein with respect to FIG. 13, in someexamples, the loading at 140 comprises loading vertical tailfin assembly332 onto empennage positioning structure 440 in loading orientation 442.As indicated in the sequence illustrated between FIGS. 13 and 17, theadjusting at 154 may comprise rotating vertical tailfin assembly 332,such as via pitch adjustment 710 utilizing rotating drive mechanisms474, from loading orientation 442 to an assembly orientation 444. Asindicated in FIG. 18, in some examples, when vertical tailfin assembly332 is in assembly orientation 444, methods 100 comprise positioning at140 horizontal stabilizer assembly 334 utilizing conveying mechanism 500proximate to vertical tailfin assembly 332 in horizontal stabilizerinstallation position 640, and assembling at 160 and/or attaching at 162vertical tailfin assembly 332 with horizontal stabilizer assembly 334 toform empennage assembly 330. Now referring to the sequence illustratedbetween FIGS. 18 and 19, in some examples, the positioning at 150, 152yet further comprises adjusting 154 empennage assembly 330, such as viapitch adjustment 710 utilizing rotating drive mechanisms 474, fromassembly orientation 444 to an installation orientation 446, andoptionally performing any additional positional adjustment(s) 700, suchas X positional adjustments 740 via drive mechanism 470, of empennageassembly 330 utilizing empennage positioning structure 440 to positionempennage assembly 330 in empennage installation position 620, which maybe described as being located at aft region 314 of fuselage assembly310.

While FIGS. 17-19 illustrate specific examples of positioning at 150 andassembling at 160 of a T-tail type empennage assembly 330, other typesof empennage assemblies 330 are within the scope of the presentdisclosure, such as fuselage mounted type empennage assemblies 330and/or cruciform type empennage assemblies 330. Likewise, thepositioning at 150 and assembling at 160 of empennage assembly 330 isnot limited to the specific order illustrated in FIGS. 17-19. Asexamples, methods 100 also may comprise loading at 130 horizontalstabilizer assembly 334 onto empennage positioning structure 440, andpositioning 150 vertical tailfin assembly 332 proximate to horizontalstabilizer assembly 334 utilizing conveying mechanism 500, andsubsequently assembling at 160 horizontal stabilizer assembly 334 withvertical tailfin assembly 332 to form empennage assembly 330. As yetmore examples, methods 100 alternatively comprises positioning at 150,152 horizontal stabilizer assembly 334 or vertical tailfin assembly 332in empennage installation position 620, and attaching horizontalstabilizer assembly 334 or vertical tailfin assembly 332 with fuselageassembly 310, prior to attaching horizontal stabilizer assembly 334 withvertical tailfin assembly 332.

FIG. 20 illustrates an example in which the positioning at 150 isperformed independent of a respective aircraft component positioningstructure and is performed manually and/or utilizing conveying mechanism500. In the specific example shown, the positioning at 150 comprisespositioning nose assembly 350 in nose installation position 650utilizing conveying mechanism 500. In some such examples, conveyingmechanism handle(s) 480 associated with conveying mechanism 500 engagewith handling fittings 392 of nose assembly 350 to facilitate thepositioning at 150. As illustrated in FIG. 20, nose installationposition 650 may be described as being located at a nose region 316 offuselage assembly 310.

Now referring to FIG. 21, in some examples the positioning at 150, 152,154 comprises positioning engine assembly(s) 340 in engine installationposition(s) 630 utilizing engine positioning structure(s) 450. In somesuch examples, engine installation position(s) 630 are generally locatedon an underside 324 of wing(s) 320, and engine positioning structure(s)450 are indexed to fuselage positioning structure 420 proximate tolateral side(s) 312 of fuselage assembly 310 beneath wing(s) 320. Inother examples, engine installation position(s) 630 are located at noseregion 316 of fuselage assembly 310, on nose assembly 350, and/or onlateral sides 312 of fuselage assembly. As discussed in relation to FIG.14, in some examples, a portion of engine shipping fixture(s) 270 areutilized in engine positioning structure(s) 450 to support engineassembly(s) 340 during the positioning at 150, 152. More specifically,as shown in the example of FIG. 21, engine positioning structure 450comprises base structure 412 that is indexed to fuselage positioningstructure 420 and vertical rise structure 414 comprising two jackmechanisms 460 that operatively engage with base structure 412. In somesuch examples, base structure 412 is configured to translate and/orextend outwardly relative to fuselage positioning structure 420 topermit Y positional adjustments 750 of engine assembly 340. As furthershown in FIG. 21, jack mechanisms 460 operatively couple to engineshipping fixture 270 and permit pitch adjustment 710, yaw adjustment720, roll adjustment 730, Y positional adjustment 750, and Z positionaladjustment 760 of engine assembly relative to engine installationposition 630. Thus, in some examples, positioning engine assembly(s) 340at 150, 152, comprises performing one or more positional adjustments 700at 154 utilizing engine positioning structure(s) 450.

Each of the jack mechanisms 460, wing jack mechanisms 462, drivemechanisms 470, push mechanisms 472, and rotating drive mechanisms 474associated with any aircraft component positioning structures 410 areconfigured to facilitate the one or more positional adjustments 700discussed herein by any suitable mechanism. For instance, in someexamples, drive mechanisms 470 and/or rotating drive mechanisms 474comprise worm drive mechanisms. As more examples, jack mechanisms 460may comprise screw jack mechanisms. Each of the jack mechanisms 460,wing jack mechanisms 462, drive mechanisms 470, push mechanisms 472, androtating drive mechanisms 474 associated with any aircraft componentpositioning structure(s) 410 also are powered by any suitable mechanismwith examples including one or more of hydraulically powered,mechanically powered, electrically powered, manually powered, and/orhand powered.

Returning to the examples of FIG. 3 and with continued reference to theexamples of FIG. 2, methods 100 further comprise assembling the aircraftcomponents as the complete aircraft by attaching each aircraft componentto at least one other aircraft component in the corresponding aircraftcomponent installation position at 160. For examples in which at least asubset of the aircraft components comprise interconnectable preinstalledportions of one or more air aircraft systems, the assembling at 160further comprises interconnecting the interconnectable portions of eachaircraft system to form one or more respective complete aircraft systemsat 162. As discussed herein, the interconnecting at 162 comprisesinterconnecting respective preinstalled portions of a given aircraftsystem by any suitable mechanism, such as by interconnecting one or morequick connects that are included in a preinstalled portion of the givenaircraft system with one or more quick connects included in one or moreother preinstalled portions of the given aircraft system. Additionallyor alternatively, for examples in which at least some of the aircraftcomponents each comprises one or more predrilled installationinterfaces, the assembling at 160 comprises attaching the aircraftcomponents through the predrilled installation interfaces. As discussedherein, attaching refers to any suitable attaching mechanism(s) foradequately joining two or more aircraft components. Examples of suitablemechanism(s) comprise one or more of fastening, coupling, fixing,bolting, screwing, welding, sealing, riveting, pinning, interlockingand/or mounting. In some examples, the assembling at 160 comprisesattaching two or more aircraft components 300 with fasteners 302.Additionally or alternatively, the assembling at 160 comprises attachingtwo or more aircraft components utilizing fastening mechanisms 404.

The assembling at 160 may be performed subsequent to the positioning at150, 152, subsequent to the adjusting at 154, prior to disengaging at170, substantially simultaneously with the disengaging at 170, prior toreloading at 180, prior to performing at 190, and/or prior to performingat 195. Examples of the assembling at 160 comprises attaching wing(s)320 to fuselage assembly 310, attaching engine assembly(s) 340 towing(s) 320, attaching vertical tailfin assembly 332 to horizontalstabilizer assembly 334, attaching empennage assembly 330 to fuselageassembly 310, attaching landing gear assembly 360 to fuselage assembly310, and/or attaching nose assembly 350 to fuselage assembly 310.

As indicated in the sequence between FIGS. 15 and 19, in some examples,the assembling at 160 comprises attaching wing(s) 320 to lateral sides312 of fuselage assembly 310 to assemble wing(s) 320 in winginstallation position(s) 610. More specifically, as shown in FIGS. 12and 15, in some examples, lateral sides 312 of fuselage assembly 310 andwing(s) 320 comprise predrilled installation interfaces 390. Thus, insuch examples, assembling 160 wing(s) with fuselage assembly comprisesattaching or coupling respective predrilled installation interfaces 390.FIG. 15 further illustrates an example in which wing(s) 320 and fuselageassembly 310 comprise interconnectable preinstalled portions of one ormore aircraft systems 394. Thus, in such examples, assembling wing(s)320 with fuselage assembly 310 comprises interconnectinginterconnectable preinstalled portions of aircraft system(s) 394 to format least a portion of the one or more respective aircraft systems at162.

Now referring to the sequence illustrated between FIGS. 17-19, in someexamples, the assembling at 160 comprises attaching horizontalstabilizer assembly 334 to vertical tailfin assembly 332 in horizontalstabilizer installation position 640 to form empennage assembly 330. Insome such examples, and as illustrated in the sequence between FIGS. 19and 22, the assembling further comprises attaching empennage assembly330 to aft region 314 of fuselage assembly 310 to assemble empennageassembly 330 in empennage installation position 620. In other examples,the assembling at 160 comprises attaching horizontal stabilizer assembly334 or vertical tailfin assembly 332 to fuselage assembly 310 prior toattaching horizontal stabilizer assembly 334 to vertical tailfinassembly 332. As further indicated FIGS. 17-19, in any such examples,each of aft region 314 of fuselage assembly 310, vertical tailfinassembly 332, horizontal stabilizer assembly 334, and/or empennageassembly 330 optionally comprise interconnectable preinstalled portionsof one or more aircraft systems 394, and thus assembling any combinationof the fuselage assembly 310, the empennage assembly 330, the verticaltailfin assembly 332, and the horizontal stabilizer assembly 334optionally comprises the interconnecting at 162. Aft region 314 offuselage assembly 310, vertical tailfin assembly 332, horizontalstabilizer assembly 334, and/or empennage assembly 330 optionallycomprise predrilled installation interfaces 390, and thus assembling anycombination of the fuselage assembly 310, the empennage assembly 330,the vertical tailfin assembly 332, and the horizontal stabilizerassembly 334 optionally comprises attaching respective predrilledinstallation interfaces 390.

Referring now to the sequence illustrated between FIGS. 21-22, in someexamples, the assembling at 160 comprises attaching engine assembly(s)340 to the underside(s) 324 of wing(s) 320 to assemble engineassembly(s) 340 in engine installation position(s) 630. As illustratedin the sequence between FIGS. 25 and 1, for examples in which engineassembly(s) 340 correspond to propeller type engines, the assembling at160 further comprises attaching propeller(s) 342 to engine assembly(s)340.

As shown in the sequence illustrated between FIGS. 20 and 23, theassembling at 160 further may comprise attaching nose assembly 350 tonose region 316 of fuselage assembly 310 to assemble nose assembly 350in nose installation position 650. As discussed in more detail withrespect to assembling 160 wing(s) 320 and empennage assembly 330, andindicated in FIGS. 20-23, assembling 160 engine assembly(s) 340 and/ornose assembly 350 further may comprise interconnecting interconnectablepreinstalled portions of aircraft systems, for example fuel systems forengine assembly(s) 340, and/or attaching the respective aircraftcomponents via predrilled installation interfaces 390.

Now referring to FIG. 22, in some examples, systems 200 comprises wingstrut(s) 326 for stabilizing wing(s) 320 of complete aircraft 800. Insuch examples, the assembling at 160 further comprises attaching eachwing strut 326 to underside 324 of a wing 320 and a correspondinglateral side 312 of fuselage assembly 310 to assemble each wing strut326 in wing strut installation position 670. In some such examples,positioning 150 wing strut(s) 326 is performed manually, and/orindependently of a respective aircraft component positioning structure410 and/or with conveying mechanism 500. Additionally or alternatively,as discussed in more detail herein with respect to installing at 172, insome examples, stabilization jacks 490 installed at underside 324 ofwing(s) 320 are utilized to perform Z positional adjustments 760 onwing(s) 320 to permit wing strut(s) 326 to be attached in wing strutinstallation position(s) 670. As shown in the example of FIG. 22, wingstrut(s) 326 are attached in wing strut installation position(s) 670 viapredrilled installation interfaces 390.

Turning to FIG. 23, for examples in which wing(s) 320 are notpreassembled with flap(s) 380, the assembling at 160 comprises attachingflap(s) 380 to wing(s) 320 to assemble flap(s) 380 in flap(s)installation position(s) 680. In some such examples, assembling 160flap(s) further comprises interconnecting interconnectable preinstalledportions of aircraft system(s) 394 of flap(s) 380 and wing(s) 320 toform at least a portion of the respective complete aircraft system(s) at162, such as a mechanical system for actuating flap(s) 380. Withcontinued reference to FIG. 23, for examples in which horizontalstabilizer assembly 334 and/or vertical tailfin assembly 332 are notpreassembled with rudder(s) 382, the assembling at 160 comprisesattaching rudder(s) 382 to one or more of horizontal stabilizer assembly334 and vertical tailfin assembly 332 to assemble rudder(s) 382 inrudder(s) installation position(s) 682. In some such examples, theassembling at 160 further comprises interconnecting 162 interconnectablepreinstalled portions of aircraft system(s) 394 comprised in rudder(s)382 and one or more of vertical tailfin assembly 332 and horizontalstabilizer assembly 334. As further illustrated in FIG. 23, theassembling at 160 further may comprise attaching aircraft fairings 370in respective aircraft fairing installation positions. As more specificexamples, the assembling at 160 of aircraft fairings 370 may compriseattaching fillet(s) between fuselage assembly 310 and wing(s) 320,attaching engine covering(s) on wing(s) 320 proximate to engineassembly(s) 340, and attaching a leading edge to empennage assembly 330.In some examples, the positioning at 150 of flap(s) 380, rudder(s) 382,and/or aircraft fairings 370 is performed manually, and/or independentlyof respective aircraft component positioning structure(s).

In some examples, systems 200 comprise landing gear assembly 360 that isconfigured to be attached to an underside region 319 of fuselageassembly 310. The examples represented in FIGS. 24-25 illustrate aspecific sequence of the indexing at 135, the positioning at 150, 152,the adjusting at 156, and the assembling at 160 that may be utilized toinstall landing gear assembly 360. With initial reference to FIG. 24, insome examples, installing landing gear assembly 360 comprises performingpositional adjustment(s) 700 on fuselage assembly 310 utilizing jackmechanism(s) 460. More specifically, in some such examples, methods 100comprise indexing at 135 jack mechanism(s) 460 to fuselage positioningstructure 420, and engaging jack mechanism(s) 460 with lift header(s)424 comprised in fuselage positioning structure 420. In the exampleshown, following the indexing at 135, the positioning at 150 of fuselageassembly 310 comprises lifting (i.e., performing Z positionaladjustments 760) fuselage assembly 310 from base structure 412 with jackmechanism(s) 460 and lift header(s) 424 to a landing gear installationposition 660. As discussed herein, the jack mechanisms 460 that areutilized to lift fuselage assembly from base structure 412 may be thesame jack mechanisms 460 that are comprised in engine positioningstructure(s) 450. Now referring to the examples of FIG. 25, oncefuselage assembly 310 is positioned in landing gear installationposition 660, the assembling at 160 comprises attaching landing gearassembly 360 to an underside region 319 of fuselage assembly 310. Insome such examples, the assembling at 160 of landing gear assembly 360comprises attaching via predrilled installation interfaces 390, and/orinterconnecting 162 interconnectable preinstalled portions of aircraftsystem(s) 394 that comprise fuselage assembly 310 and landing gearassembly 360. As indicated in the sequence illustrated between FIGS. 25and 1, in some examples the assembling at 160 further comprisesattaching aircraft fairing(s) 370 to portions of landing gear assembly360.

Turning back to FIG. 3, in some examples, methods 100 comprisedisengaging aircraft component positioning structure(s) from therespective aircraft component(s) at 170. In some such examples, thedisengaging at 170 comprises installing stabilization jacks at 172 tostabilize the respective aircraft component(s) during and/or followingthe disengaging at 170. Thus, the installing at 172 may be performedprior to, substantially simultaneously with, and/or subsequent to thedisengaging at 170. The disengaging at 170 and/or the installing at 172may be performed substantially simultaneously with the assembling at160, subsequent to the assembling at 160, prior to the reloading at 180,prior to the performing at 190, and/or prior to the performing at 195.

In some examples, the disengaging at 170 is performed such that aparticular portion of the partially assembled aircraft is accessibleduring subsequent steps of methods 100. Additionally or alternatively,the disengaging at 170 is performed to permit the performance of qualityanalysis and/or flight test on the complete aircraft. As such, thedisengaging at 170 may comprise disengaging each aircraft componentpositioning structure that is utilized in connection with methods 100from the partially assembled aircraft and/or the complete aircraft. As amore specific example, when an aircraft component positioning structurewas engaged with the fuselage positioning structure during the indexingat 135, the disengaging at 170 further comprises disengaging theaircraft component positioning structure from the fuselage positioningstructure.

The sequence illustrated between FIGS. 15 and 17 provides a specificexample of the disengaging at 170 and the installing at 172. As shown,in some examples, methods 100 comprise disengaging 170 wing positioningstructure(s) 430 from wing(s) 320. In some such examples, thedisengaging at 170 comprises installing 172 stabilization jacks 490 tosupport wing(s) 320 during subsequent steps of methods 100. As shown inFIG. 22, in some examples, stabilization jacks 490 are configured topermit one or more positional adjustments 700, such as Z positionaladjustments 760, of the supported aircraft component(s) 300.

Referring again to the examples of FIG. 3 and with continued referenceto FIG. 2, methods 100 optionally comprise reloading tooling 400 intothe one or more shipping containers at 180. In some examples, thereloading at 180 is performed to permit tooling 400 to be shipped fromthe assembly location to be reused at another location for assembly ofanother containerized aircraft. With this in mind, tooling 400 may beconfigured to be reloaded into shipping containers. The reloading at 180may comprise reloading a portion of, such as one or more aircraftcomponent positioning structures 410, or the entirety of the tooling400. With specific reference to aircraft component positioningstructure(s) 410, the reloading at 180 may be performed subsequent tothe positioning at 152, subsequent to the assembling at 160, subsequentto the disengaging at 170, prior to the performing at 190, 195, and/orsubsequent to the performing at 190, 195.

As further illustrated in the examples of FIG. 3, methods 100 optionallycomprise performing one or more quality analyses at 190. In some suchexamples, the methods 100 comprise performing the quality analyses 190on portions of the partially assembled aircraft. Additionally oralternatively, methods 100 comprise performing quality analyses 190 onthe complete aircraft. Methods 100 also may comprise performing a flighttest and/or flight certification on the complete aircraft at 195. Insome examples, the performing at 190 and/or the performing at 195 isperformed at the assembly location. The performing at 190 may beperformed subsequent to the disengaging 170, subsequent to theassembling at 160, and/or prior to the performing at 195. The performingat 195 may be performed subsequent to the disengaging 170, subsequent tothe assembling at 160, and/or subsequent to the performing at 190.Performing the quality analysis at 190 may be executed to determinewhether the assembling of each aircraft component was executed properly,such that the complete aircraft passes one or more specifications.Likewise, performing the flight test at 195 may be executed to determinewhether the complete aircraft passes one or more operationalspecifications. The performing at 190 and the performing at 195 may beperformed by the one or more authorized personnel. As discussed herein,the one or more authorized personnel may be employed by, authorized by,and/or trained by the same party that performs one or more of steps 80,90, and 110 of methods 100.

Illustrative, non-exclusive examples of inventive subject matteraccording to the present disclosure are described in the followingenumerated paragraphs:

A1. A method for assembling a containerized aircraft as a completeaircraft, the method comprising:

removing a plurality of aircraft components supported on one or moreshipping fixtures from one or more shipping containers;

removing tooling from the one or more shipping containers, wherein thetooling comprises one or more aircraft component positioning structures;

unloading each aircraft component of the plurality of aircraftcomponents from the one or more shipping fixtures;

loading one or more aircraft components of the plurality of aircraftcomponents onto one or more respective aircraft component positioningstructures;

positioning each aircraft component of the plurality of aircraftcomponents in a corresponding aircraft component installation position,wherein the positioning comprises positioning the one or more aircraftcomponents using the one or more respective aircraft componentpositioning structures; and

assembling the plurality of aircraft components as the complete aircraftby attaching each aircraft component of the plurality of aircraftcomponents to at least one other aircraft component of the plurality ofaircraft components in the corresponding aircraft component installationposition.

A2. The method of paragraphs A1, wherein the plurality of aircraftcomponents comprises a fuselage assembly, one or more wings, one or moreengine assemblies, a vertical tailfin assembly, a horizontal stabilizerassembly, and a landing gear assembly.

A3. The method of paragraph A2, wherein the plurality of aircraftcomponents further comprises and a plurality of aircraft fairings, oneor more flaps, one or more rudders, and a nose assembly.

A4. The method of any of paragraphs A1-A3, wherein the removingcomprises engaging a shipping fixture of the one or more shippingfixtures to convey the shipping fixture and at least a subset of theplurality of aircraft components that are supported on the shippingfixture from a shipping container of the one or more shippingcontainers.

A5. The method of any of paragraphs A1-A4, wherein the plurality ofaircraft components comprises one or more wings, and wherein theunloading comprises unloading a wing of the one or more wings from awing shipping fixture by pivoting a hinged wing support member of thewing shipping fixture from a shipping orientation, in which the wing issupported by the hinged wing support member with a chord of the wingbeing oriented upwardly, to an unloading orientation, in which the wingis supported by the hinged wing support member with the chord of thewing being oriented outwardly.

A6. The method of paragraph A5, wherein the unloading the wing furthercomprises lifting the wing in the unloading orientation from the fromthe wing shipping fixture with a/the conveying mechanism.

A7. The method of any of paragraphs A5-A6, wherein the unloadingcomprises unloading a vertical tailfin assembly from the wing shippingfixture by lifting the vertical tailfin assembly from the wing shippingfixture using a/the conveying mechanism.

A8. The method of any of paragraphs A1-A7, wherein the one or moreaircraft component positioning structures comprises a fuselagepositioning structure for supporting and positioning the fuselageassembly, and wherein the method further comprises:

indexing at least one other aircraft component positioning structure ofthe one or more aircraft component positioning structures relative tothe fuselage positioning structure.

A8.1 The method of any of paragraphs A1-A8, wherein the one or moreshipping fixtures comprise a fuselage shipping fixture, and wherein thefuselage shipping fixture is used as a fuselage positioning structure.

A9. The method of paragraph A8, wherein the indexing comprisespositioning the at least one other aircraft component positioningstructure proximate to the corresponding aircraft component installationposition.

A10. The method of any of paragraph A9, where the indexing furthercomprises engaging a base structure of the fuselage positioningstructure and a base structure of the at least one other aircraftcomponent positioning structure.

A11. The method of any of paragraphs A8-A10, wherein the indexingcomprises indexing one or more wing positioning structures proximate toone or more lateral sides of the fuselage assembly.

A12. The method of any of paragraphs A8-A11, wherein the indexingcomprises indexing an empennage positioning structure proximate to anaft region of the fuselage assembly.

A13. The method of any of paragraphs A1-A12, further comprising:

releasably engaging a conveying mechanism handle associated with aconveying mechanism with a handling fitting of an aircraft component ofthe plurality of aircraft components;

unloading the aircraft component from a shipping fixture of the one ormore shipping fixtures using the conveying mechanism; and

loading the aircraft component onto the respective aircraft componentpositioning structure using the conveying mechanism.

A13.1 The method of paragraph A13, wherein the conveying mechanismcomprises a forklift and the conveying mechanism handle comprises aforklift boom handle.

A14. The method of any of paragraphs A1-A13.1, wherein the loadingcomprises loading a/the one or more wings onto one or more respectivewing positioning structures.

A15. The method of any of paragraphs A1-A14, wherein the loadingcomprises loading a/the vertical tailfin assembly onto an/the empennagepositioning structure.

A16. The method of paragraph A15, wherein the loading further comprisesoperating a/the conveying mechanism to load the vertical tailfinassembly onto the empennage positioning structure.

A17. The method of any of paragraphs A15-A16, wherein loading thevertical tailfin assembly comprises loading the vertical tailfinassembly in a loading orientation, and wherein the positioning comprisesrotating the vertical tailfin assembly with the empennage positioningstructure from the loading orientation to an assembly orientation.

A18. The method of any of paragraphs A1-A14, wherein the loading furthercomprises loading a horizontal stabilizer assembly onto an/the empennagepositioning structure.

A19. The method of any of paragraphs A1-A18, wherein the positioningcomprises performing one or more positional adjustments on an aircraftcomponent of the one or more aircraft components relative to thecorresponding aircraft component installation position using therespective aircraft component positioning structure, and wherein the oneor more positional adjustments comprise one or more of a pitchadjustment, a roll adjustment, a yaw adjustment, an X positionaladjustment, a Y positional adjustment, and a Z positional adjustment.

A19.1. The method of any of paragraphs A1-A19, wherein, at least asubset of aircraft component positioning structures of the one or moreaircraft component positioning structures comprises a base structure anda vertical rise structure, wherein the base structure is configured tosupport the respective aircraft component positioning structure on anassembly surface, and wherein the vertical rise structure extendsupwardly from the base structure and is configured to support the atleast one respective aircraft component.

A19.2 The method of paragraph A19.1, wherein each aircraft componentpositioning structure of the subset of aircraft component positioningstructures further comprises:

one or more drive mechanisms associated with the vertical rise structurethat are configured to facilitate translation of the vertical risestructure along the base structure to permit each aircraft componentpositioning structure of the subset of aircraft component positioningstructures to facilitate one of an X positional adjustment or a Ypositional adjustment of at least one respective aircraft component ofthe plurality of aircraft components; and

one or more jack mechanisms associated with the vertical rise structurethat are configured to permit each aircraft component positioningstructure of the subset of aircraft component positioning structures tofacilitate a Z positional adjustment of the at least one respectiveaircraft component of the plurality of aircraft components.

A20. The method of any of paragraphs A1-A19.1, wherein the positioningcomprises positioning two or more aircraft components of the pluralityof aircraft components using a single aircraft component positioningstructure of the one or more aircraft component positioning structure.

A20.1 The method of any of paragraphs A1-A20, wherein the positioningcomprises utilizing one or more jack mechanisms comprising a particularaircraft component positioning structure in another aircraft componentpositioning structure.

A21. The method of any of paragraphs A1-A20.1, wherein the positioningcomprises positioning a/the one or more wings in one or morecorresponding wing installation positions using one or more respectivewing positioning structures.

A22. The method of paragraph A21, wherein the one or more winginstallation positions are located on one or more lateral sides of thefuselage assembly.

A23. The method of any of paragraphs A1-22, wherein the positioningcomprises positioning one of an empennage assembly, a/the verticaltailfin assembly, and a/the horizontal stabilizer assembly in anempennage installation position using the empennage positioningstructure.

A24. The method of paragraph A23, wherein the empennage installationposition is located at an/the aft region of the fuselage assembly.

A25. The method of any of paragraphs A1-A24, wherein the positioningcomprises positioning one or more engine assemblies in one or morecorresponding engine assembly installation positions.

A26. The method of paragraph A25, wherein the one or more engineassembly installation positions are located on the one or more wings.

A27. The method of any of paragraphs A25-A26, wherein the positioningfurther comprises positioning the one or more engine assemblies usingone or more respective engine assembly positioning structures.

A28. The method of any of paragraphs A1-A27, wherein the positioningcomprises lifting a/the fuselage assembly from a base structure of a/thefuselage positioning structure to a desired landing gear installationheight by engaging one or more jack mechanisms with one or more liftheaders comprising the fuselage positioning structure.

A29. The method of any of paragraphs A1-A28, wherein the positioningcomprises positioning a/the nose assembly proximate to a nose region ofthe fuselage assembly in a nose installation position.

A30. The method of paragraph A29, wherein the positioning of the noseassembly comprises positioning using a/the conveying mechanism.

A31. The method of any of paragraphs A1-A30, wherein the assemblingcomprises interconnecting interconnectable preinstalled portions of oneor more aircraft systems that comprise at least a subset of theplurality of aircraft components to form one or more respective completeaircraft systems.

A31.1 The method of any of paragraphs A1-A30, wherein each aircraftcomponent of at least a subset of the plurality of aircraft componentscomprises one or more predrilled installation interfaces, and whereinthe assembling further comprises attaching each aircraft component ofthe subset of the plurality of aircraft components to at least one otheraircraft component through the one or more predrilled installationinterfaces.

A32. The method of any of paragraphs A1-A31, wherein the assemblingcomprises attaching a/the one or more wings to the one or more lateralsides of the fuselage assembly to assemble the one or more wings in theone or more corresponding wing installation positions.

A33. The method of any of paragraphs A1-A32, wherein the assemblingcomprises attaching a/the empennage assembly to a/the aft region of thefuselage assembly to assemble the empennage assembly in the empennageinstallation position.

A34. The method of any of paragraphs A2-A33, wherein the assemblingcomprises attaching a/the horizontal stabilizer assembly to a/thevertical tailfin assembly in a horizontal stabilizer installationposition to form a/the empennage assembly.

A35. The method of any of paragraphs A1-A34, wherein the assemblingcomprises attaching the horizontal stabilizer assembly to a/the aftregion of the fuselage assembly to assemble the horizontal stabilizerassembly in the empennage installation position.

A35.1 The method of any of paragraphs A1-A34, wherein the plurality ofaircraft components comprises a fuselage assembly, a vertical tailfinassembly and a horizontal stabilizer assembly, wherein the methodfurther comprises:

positioning the vertical tailfin assembly in a vertical tailfininstallation position using an empennage positioning structure;

positioning the horizontal stabilizer assembly in a horizontalstabilizer installation position utilizing a conveying mechanism;

attaching the horizontal stabilizer assembly with the vertical tailfinassembly to form an empennage assembly;

performing positional adjustments on the empennage assembly using theempennage positioning structure to position the empennage assembly in anempennage installation position; and

attaching the empennage assembly to the fuselage assembly to assemblethe empennage assembly in an empennage assembly installation position.

A36. The method of any of paragraphs A1-A35.1, wherein the assemblingcomprises attaching one or more engine assemblies to one or more wingsto assemble the engine assemblies in the one or more correspondingengine assembly installation positions.

A37. The method of any of paragraphs A1-A36, wherein the assemblingcomprises attaching a/the landing gear assembly to an underside regionof a/the fuselage assembly to assemble the landing gear assembly in oneor more landing gear assembly installation positions.

A38. The method of any of paragraphs A1-A37, further comprisingdisengaging the one or more aircraft components positioning structuresfrom the one or more respective aircraft components.

A39. The method of paragraph A38, further comprising installing one ormore stabilization jacks prior to the disengaging.

A40. The method of any of paragraphs A1-A39, further comprisingreloading the tooling assembly into the one or more shipping containers.

A41. The method of any of paragraphs A1-A40, further comprisingperforming a quality analysis of the complete aircraft.

A42. The method of any of paragraphs A1-A41, wherein the method isperformed at an assembly location.

A43. The method of any of paragraphs A1-A42, further comprisingperforming a flight test and certification at a/the assembly location.

B1. The method of any of paragraphs A1-A43, further comprising using asystem of any paragraphs C1-C36 to assemble the complete aircraft.

B2. The method of any of paragraphs A1-A43, further comprisingdelivering a/the system of any paragraphs C1-C36 to a/the assemblylocation.

C1. A system for assembling a containerized aircraft as a completeaircraft, the system comprising:

a plurality of aircraft components that are configured to be loaded intoone or more shipping containers in a shipping arrangement, and whereineach aircraft component of the plurality of aircraft components isconfigured to be unloaded from the shipping arrangement and attached toat least one other aircraft component of the plurality of aircraftcomponents to assemble the plurality of aircraft components into thecomplete aircraft;

one or more shipping fixtures configured to support the plurality ofaircraft components in the shipping arrangement; and

tooling configured to facilitate assembly of the plurality of aircraftcomponents into the complete aircraft, wherein the tooling is configuredto be loaded into and unloaded from the one or more shipping containers,wherein the tooling comprises one or more aircraft component positioningstructures, and wherein each aircraft component positioning structure ofthe one or more aircraft component positioning structures is configuredto position at least one respective aircraft component of the pluralityof aircraft components in at least one corresponding aircraft componentinstallation position during assembly of the complete aircraft.

C2. The system of paragraph C1, wherein the plurality of aircraftcomponents comprises a fuselage assembly, one or more wings, one or moreengine assemblies, a vertical tailfin assembly, a horizontal stabilizerassembly, and a landing gear assembly.

C3. The system of paragraph C2, wherein the plurality of aircraftcomponents further comprises a nose assembly.

C4. The system of any of paragraphs C2-C3, wherein the plurality ofaircraft components further comprises a plurality of aircraft fairings,one or more flaps, and one or more rudders.

C5. The system of any of paragraphs C1-C4, wherein at least a subset ofthe plurality of aircraft components comprises interconnectablepreinstalled portions of one or more aircraft systems.

C6. The system of paragraph C5, wherein the interconnectablepreinstalled portions of each aircraft system of the one or moreaircraft systems are configured to be interconnected to form a completeaircraft system.

C7. The system of any of paragraphs C1-C6, wherein each aircraftcomponent of at least a subset of the plurality of aircraft componentscomprises one or more predrilled installation interfaces configured topermit a drilling-free attachment of each aircraft component of thesubset of the plurality of the aircraft components.

C8. The system of any of paragraphs C1-C7, wherein one or more aircraftcomponents of the plurality of aircraft components comprises one or morehandling fittings configured to releasably engage with a conveyingmechanism.

C9. The system of paragraph C8, wherein the one or more handlingfittings are configured to releasably engage with at least one conveyingmechanism handle of the one or more conveying mechanism handles.

C10. The system of any of paragraphs C1-C9, further comprising the oneor more shipping containers.

C11. The system of any of paragraphs C1-C10, wherein a/the fuselageassembly comprises an open internal volume, and wherein one or moreaircraft components of the plurality of aircraft components areconfigured to be received within the open internal volume of thefuselage assembly when the plurality of aircraft components are arrangedin the shipping arrangement.

C12. The system of paragraph C11, wherein the one or more aircraftcomponents comprises a/the horizontal stabilizer assembly and one ormore engine assemblies, and wherein the horizontal stabilizer assemblyis supported by a empennage shipping fixture, and wherein the one ormore engine assemblies are supported by an engine shipping fixture.

C13. The system of any of paragraphs C1-C12, wherein the one or moreshipping fixtures comprises a fuselage shipping fixture that isconfigured to support and arrange a/the fuselage assembly in theshipping arrangement.

C14. The system of any of paragraphs C1-C13, wherein the one or moreshipping fixtures comprises a wing shipping fixture that is configuredto support and arrange one or more wings in the one or more shippingcontainers.

C15. The system of any of paragraphs C1-C14, wherein the wing shippingfixture further is configured to support and arrange a/the nose assemblyin the shipping arrangement.

C16. The system of any of paragraphs C14-C15, wherein the wing shippingfixture comprises a hinged wing support member that is configured tooperatively support a wing of the one or more wings, wherein the hingedwing support member is configured to pivot between a shippingorientation and an unloading orientation, wherein the hinged wingsupport member is configured to support the wing with a chord of thewing oriented upwardly in the shipping orientation, and wherein thehinged wing support member is configured to support the wing with thechord of the wing oriented outwardly in the unloading orientation.

C17. The system of paragraph C16, wherein the hinged wing support memberis a first hinged wing support member, and wherein the wing shippingfixture further comprises a second hinged wing support member.

C18. The system of any of paragraphs C16-C17, wherein the wing isconfigured to be unloaded from the wing shipping fixture in theunloading orientation.

C19. The system of any of paragraphs C1-C18, wherein the tooling isconfigured to be manually operated, and wherein the tooling isconfigured to be operated independent of computer aided systems.

C20. The system of any of paragraphs C1-C19, wherein the tooling isconfigured to facilitate the assembly of the plurality of aircraftcomponents into the complete aircraft in a plurality of assemblyenvironments.

C21. The system of paragraph C20, wherein each assembly environment ofthe plurality of assembly environments comprises an assembly surface,wherein the assembly surface comprises one or more of an uneven assemblysurface, a dirt assembly surface, a grassy assembly surface, anunfinished assembly surface, and a wet assembly surface.

C22. The system of any of paragraphs C1-C21, wherein the system furthercomprises a/the conveying mechanism configured to convey the one or moreaircraft components of the plurality of aircraft components from arespective shipping fixture of the one or more shipping fixture to arespective aircraft component positioning structure.

C23. The system of any of paragraphs C1-C22, wherein the conveyingmechanism further is configured to convey the one or more shippingfixtures from the one or more shipping containers.

C24. The system of any of paragraphs C22-C23, wherein the conveyingmechanism comprises a forklift.

C25. The system of any of paragraphs C1-C24, wherein the toolingcomprises one or more conveying mechanism handles, wherein eachconveying mechanism handle is configured to associate with the conveyingmechanism and releasably engage with one or more respective handlingfittings.

C26. The system of any of paragraphs C22-C25, wherein the one or moreconveying mechanism handles comprise at least one forklift boom handle.

C27. The system of any of paragraphs C1-C26, wherein at least oneaircraft component positioning structure of the one or more aircraftcomponent positioning structures is configured to position two or moreaircraft components of the plurality of aircraft components.

C28. The system of any of paragraphs C1-C27, wherein the plurality ofaircraft component positioning structures comprises one or more wingpositioning structures.

C29. The system of any of paragraphs C1-C28, wherein the plurality ofaircraft component positioning structures comprises an empennagepositioning structure.

C30. The system of any of paragraphs C1-C29, wherein at least one of theone or more aircraft component positioning structures comprises a basestructure and vertical rise structure, wherein the base structure isconfigured to support the vertical rise structure on an/the assemblysurface and comprises a laterally extending track, wherein the verticalrise structure extends upwardly from the laterally extending track andis configured to operatively support the at least one respectiveaircraft components.

C31. The system of any of paragraphs C1-C30, wherein at least one of theone or more aircraft component positioning structures is configured tofacilitate one or more positional adjustments of the at least onerespective aircraft component of the plurality of aircraft components,wherein the one or more positional adjustments comprise one or more of apitch adjustment, a yaw adjustment, a roll adjustment, an X positionaladjustment, a Y positional adjustment, and a Z positional adjustment.

C32. The system of paragraphs C1-C31, wherein the plurality of aircraftcomponent positioning structures comprises a fuselage positioningstructure.

C33. The system of paragraph C32, wherein the fuselage positioningstructure comprises the fuselage shipping fixture.

C34. The system of any of paragraphs C1-C33, wherein the plurality ofaircraft component positioning structures comprises one or more enginepositioning structures, and wherein each engine positioning structure isconfigured to facilitate one or more positional adjustments of an engineassembly of a/the one or more engine assemblies, wherein the one or morepositional adjustments comprise one or more of a/the pitch adjustment,a/the yaw adjustment, a/the roll adjustment, an/the X positionaladjustment, a/the Y positional adjustment, and a/the Z positionaladjustment.

C35. The system of any of paragraphs C1-C34, wherein each of a/the oneor more engine positioning structures, a/the one or more wingpositioning structures, and an/the empennage positioning structurecomprise one or more jack mechanisms that are configured to facilitatethe one or more positional adjustments of the at least one respectiveaircraft components.

C36. The system of any of paragraphs C1-C35, wherein each of a/the oneor more wing positioning structures and an/the empennage positioningstructures comprise one or more drive mechanisms that are configured tofacilitate the one or more positional adjustments of the at least onerespective aircraft components.

D1. A method for assembling a containerized aircraft as a completeaircraft, the method comprising:

removing a plurality of aircraft components supported on one or moreshipping fixtures from one or more shipping containers, wherein theplurality of aircraft components comprises one or more wings, one ormore engine assemblies, a vertical tailfin assembly, and a horizontalstabilizer assembly;

removing tooling from the one or more shipping containers, wherein thetooling comprises a plurality of aircraft component positioningstructures, and wherein the plurality of aircraft component positioningstructures comprises a fuselage positioning structure, one or more wingpositioning structures, one or more engine positioning structures, andan empennage positioning structure;

unloading each aircraft component of the plurality of aircraftcomponents from the one or more shipping fixtures;

indexing the one or more wing positioning structures to the fuselagepositioning structure proximate to lateral portions of a fuselageassembly;

loading the one or more wings onto the one or more wing positioningstructures;

positioning the one or more wings in one or more corresponding winginstallation positions using the one or more wing positioningstructures;

attaching the one or more wings to the fuselage assembly;

indexing the empennage positioning structure to the fuselage positioningstructure proximate to an aft region of the fuselage assembly;

loading the vertical tailfin assembly onto the empennage positioningstructure;

attaching the horizontal stabilizer assembly to the vertical tailfinassembly on the empennage positioning structure to form an empennageassembly;

positioning the empennage assembly in a corresponding empennageinstallation position using the empennage positioning structure;

attaching the empennage assembly to the fuselage assembly;

indexing the one or more engine positioning structures to the fuselagepositioning structure proximate to one or more lateral portions of thefuselage assembly beneath the one or more wings;

loading the one or more engine assemblies onto the one or more enginepositioning structures;

positioning the one or more engine assemblies in one or morecorresponding engine assembly installation positions using the one ormore engine positioning structures; and

attaching the one or more engine assemblies to the one or more wings.

E1. A method of preassembling and delivering a system for assembling acontainerized aircraft as a complete aircraft, the method comprising:

preassembling each aircraft component of a plurality of aircraftcomponents from a respective set of subcomponents;

loading the plurality of aircraft components and a tooling onto one ormore shipping fixtures in a shipping arrangement;

loading the one or more shipping fixtures supporting the tooling and theplurality of aircraft components into one or more shipping containers;and

delivering the one or more shipping containers from a delivery locationto an assembly location.

E2. The method of paragraph E1, further comprising preassembling thetooling, wherein the tooling is configured to facilitate assembly of theplurality of aircraft components as the complete aircraft, and whereinthe preassembling the tooling comprises preassembling one or moreaircraft component positioning structures.

E3. The method of any of paragraphs E1-E2 further comprising, the methodof any of paragraphs A1-A43.

E4. The method of any of paragraphs E1-E2 further comprising, the methodof paragraph D1.

E5. The method of any of paragraphs E1-E4, wherein the system comprisesthe system of any of paragraphs C1-C36.

As used herein, the term “and/or” placed between a first entity and asecond entity means one of (1) the first entity, (2) the second entity,and (3) the first entity and the second entity. Multiple entities listedwith “and/or” should be construed in the same manner, i.e., “one ormore” of the entities so conjoined. Other entities may optionally bepresent other than the entities specifically identified by the “and/or”clause, whether related or unrelated to those entities specificallyidentified. Thus, as a non-limiting example, a reference to “A and/orB,” when used in conjunction with open-ended language such as“comprising” may refer, in one embodiment, to A only (optionallyincluding entities other than B); in another embodiment, to B only(optionally including entities other than A); in yet another embodiment,to both A and B (optionally including other entities). These entitiesmay refer to elements, actions, structures, steps, operations, values,and the like.

As used herein, the phrase “at least one,” in reference to a list of oneor more entities should be understood to mean at least one entityselected from any one or more of the entities in the list of entities,but not necessarily including at least one of each and every entityspecifically listed within the list of entities and not excluding anycombinations of entities in the list of entities. This definition alsoallows that entities may optionally be present other than the entitiesspecifically identified within the list of entities to which the phrase“at least one” refers, whether related or unrelated to those entitiesspecifically identified. Thus, as a non-limiting example, “at least oneof A and B” (or, equivalently, “at least one of A or B,” or,equivalently “at least one of A and/or B”) may refer, in one embodiment,to at least one, optionally including more than one, A, with no Bpresent (and optionally including entities other than B); in anotherembodiment, to at least one, optionally including more than one, B, withno A present (and optionally including entities other than A); in yetanother embodiment, to at least one, optionally including more than one,A, and at least one, optionally including more than one, B (andoptionally including other entities). In other words, the phrases “atleast one,” “one or more,” and “and/or” are open-ended expressions thatare both conjunctive and disjunctive in operation. For example, each ofthe expressions “at least one of A, B, and C,” “at least one of A, B, orC,” “one or more of A, B, and C,” “one or more of A, B, or C,” and “A,B, and/or C” may mean A alone, B alone, C alone, A and B together, A andC together, B and C together, A, B, and C together, and optionally anyof the above in combination with at least one other entity.

As used herein, “at least substantially,” when modifying a degree orrelationship, includes not only the recited “substantial” degree orrelationship, but also the full extent of the recited degree orrelationship. A substantial amount of a recited degree or relationshipmay include at least 75% of the recited degree or relationship. Forexample, an object that is at least substantially formed from a materialincludes an object for which at least 75% of the object is formed fromthe material and also includes an object that is completely formed fromthe material. As another example, a first direction that is at leastsubstantially parallel to a second direction includes a first directionthat forms an angle with respect to the second direction that is at most22.5 degrees and also includes a first direction that is exactlyparallel to the second direction. As another example, a first lengththat is substantially equal to a second length includes a first lengththat is at least 75% of the second length, a first length that is equalto the second length, and a first length that exceeds the second lengthsuch that the second length is at least 75% of the first length.

As used herein, the phrase, “for example,” the phrase, “as an example,”and/or simply the term “example,” when used with reference to one ormore components, features, details, structures, embodiments, and/ormethods according to the present disclosure, are intended to convey thatthe described component, feature, detail, structure, embodiment, and/ormethod is an illustrative, non-exclusive example of components,features, details, structures, embodiments, and/or methods according tothe present disclosure. Thus, the described component, feature, detail,structure, embodiment, and/or method is not intended to be limiting,required, or exclusive/exhaustive; and other components, features,details, structures, embodiments, and/or methods, including structurallyand/or functionally similar and/or equivalent components, features,details, structures, embodiments, and/or methods, are also within thescope of the present disclosure.

As used herein the terms “adapted” and “configured” mean that theelement, component, or other subject matter is designed and/or intendedto perform a given function. Thus, the use of the terms “adapted” and“configured” should not be construed to mean that a given element,component, or other subject matter is simply “capable of” performing agiven function but that the element, component, and/or other subjectmatter is specifically selected, created, implemented, utilized,programmed, and/or designed for the purpose of performing the function.It is also within the scope of the present disclosure that elements,components, and/or other recited subject matter that is recited as beingadapted to perform a particular function may additionally oralternatively be described as being configured to perform that function,and vice versa.

The various disclosed elements of apparatuses and steps of methodsdisclosed herein are not required to all apparatuses and methodsaccording to the present disclosure, and the present disclosure includesall novel and non-obvious combinations and subcombinations of thevarious elements and steps disclosed herein. Moreover, one or more ofthe various elements and steps disclosed herein may define independentinventive subject matter that is separate and apart from the whole of adisclosed apparatus or method. Accordingly, such inventive subjectmatter is not required to be associated with the specific apparatusesand methods that are expressly disclosed herein, and such inventivesubject matter may find utility in apparatuses and/or methods that arenot expressly disclosed herein.

The invention claimed is:
 1. A method for assembling a containerizedaircraft as a complete aircraft, the method comprising: removing aplurality of aircraft components supported on one or more shippingfixtures from one or more shipping containers; removing tooling from theone or more shipping containers, wherein the tooling comprises one ormore aircraft component positioning structures; unloading each aircraftcomponent of the plurality of aircraft components from the one or moreshipping fixtures; loading one or more aircraft components of theplurality of aircraft components onto one or more respective aircraftcomponent positioning structures; positioning each aircraft component ofthe plurality of aircraft components in a corresponding aircraftcomponent installation position, wherein the positioning comprisespositioning the one or more aircraft components using the one or morerespective aircraft component positioning structures; and assembling theplurality of aircraft components as the complete aircraft by attachingeach aircraft component of the plurality of aircraft components to atleast one other aircraft component of the plurality of aircraftcomponents in the corresponding aircraft component installationposition.
 2. The method of claim 1, wherein the plurality of aircraftcomponents comprises a fuselage assembly, one or more wings, one or moreengine assemblies, a vertical tailfin assembly, a horizontal stabilizerassembly, and a landing gear assembly.
 3. The method of claim 1, whereinthe removing the plurality of aircraft components comprises engaging ashipping fixture of the one or more shipping fixtures to convey theshipping fixture and at least a subset of the plurality of aircraftcomponents that are supported on the shipping fixture from a shippingcontainer of the one or more shipping containers.
 4. The method of claim1, wherein the plurality of aircraft components comprises one or morewings, and wherein the unloading comprises unloading a wing of the oneor more wings from a wing shipping fixture by pivoting a hinged wingsupport member of the wing shipping fixture from a shipping orientation,in which the wing is supported by the hinged wing support member with achord of the wing being oriented upwardly, to an unloading orientation,in which the wing is supported by the hinged wing support member withthe chord of the wing being oriented outwardly.
 5. The method of claim1, wherein the one or more aircraft component positioning structurescomprises a fuselage positioning structure for supporting andpositioning a fuselage assembly, and wherein the method furthercomprises: indexing at least one other aircraft component positioningstructure of the one or more aircraft component positioning structuresrelative to the fuselage positioning structure.
 6. The method of claim5, wherein the indexing comprises: positioning the at least one otheraircraft component positioning structure proximate to the correspondingaircraft component installation position; and engaging a base structureof the fuselage positioning structure and a base structure of the atleast one other aircraft component positioning structure.
 7. The methodof claim 1, wherein the positioning comprises performing one or morepositional adjustments on an aircraft component of the one or moreaircraft components relative to the corresponding aircraft componentinstallation position using the respective aircraft componentpositioning structure.
 8. The method of claim 7, wherein the one or morepositional adjustments include one or more of a pitch adjustment, a rolladjustment, a yaw adjustment, an X positional adjustment, a Y positionaladjustment, and a Z positional adjustment.
 9. The method of claim 1,wherein at least a subset of aircraft component positioning structuresof the one or more aircraft component positioning structures comprises abase structure and a vertical rise structure, wherein the base structureis configured to support the respective aircraft component positioningstructure on an assembly surface, and wherein the vertical risestructure extends upwardly from the base structure and is configured tosupport the at least one respective aircraft component.
 10. The methodof claim 9, wherein each aircraft component positioning structure of thesubset of aircraft component positioning structures further comprises:one or more drive mechanisms associated with the vertical rise structurethat are configured to facilitate translation of the vertical risestructure along the base structure to permit each aircraft componentpositioning structure of the subset of aircraft component positioningstructures to facilitate one of an X positional adjustment or a Ypositional adjustment of at least one respective aircraft component ofthe plurality of aircraft components; and one or more jack mechanismsassociated with the vertical rise structure that are configured topermit each aircraft component positioning structure of the subset ofaircraft component positioning structures to facilitate a Z positionaladjustment of the at least one respective aircraft component of theplurality of aircraft components.
 11. The method of claim 1, wherein theassembling comprises interconnecting interconnectable preinstalledportions of one or more aircraft systems that comprise at least a subsetof the plurality of aircraft components to form one or more respectivecomplete aircraft systems.
 12. The method of claim 1, wherein eachaircraft component of at least a subset of the plurality of aircraftcomponents comprises one or more predrilled installation interfaces, andwherein the assembling further comprises attaching each aircraftcomponent of the subset of the plurality of aircraft components to atleast one other aircraft component through the one or more predrilledinstallation interfaces.
 13. The method of claim 1, wherein theplurality of aircraft components comprise a fuselage assembly, avertical tailfin assembly and a horizontal stabilizer assembly, whereinthe method further comprises: positioning the vertical tailfin assemblyin a vertical tailfin installation position using an empennagepositioning structure; positioning the horizontal stabilizer assembly ina horizontal stabilizer installation position utilizing a conveyingmechanism; attaching the horizontal stabilizer assembly with thevertical tailfin assembly to form an empennage assembly; performingpositional adjustments on the empennage assembly using the empennagepositioning structure to position the empennage assembly in an empennageinstallation position; and attaching the empennage assembly to thefuselage assembly to assemble the empennage assembly in an empennageassembly installation position.
 14. The method of claim 1, wherein thepositioning comprises utilizing one or more jack mechanisms comprising aparticular aircraft component positioning structure in another aircraftcomponent positioning structure.
 15. The method of claim 1, wherein theone or more shipping fixtures comprise a fuselage shipping fixture, andwherein the fuselage shipping fixture is used as a fuselage positioningstructure.
 16. The method of claim 1, further comprising: releasablyengaging a conveying mechanism handle associated with a conveyingmechanism with a handling fitting of an aircraft component of theplurality of aircraft components; unloading the aircraft component froma shipping fixture of the one or more shipping fixtures using theconveying mechanism; and loading the aircraft component onto therespective aircraft component positioning structure using the conveyingmechanism.
 17. The method of claim 16, wherein the conveying mechanismcomprises a forklift and the conveying mechanism handle comprises aforklift boom handle.
 18. The method of claim 1, further comprisingperforming one or more of a quality analyses on the complete aircraft atan assembly location, and performing a flight test on the completeaircraft at the assembly location.
 19. The method of claim 1, whereineach aircraft component of the plurality of aircraft components isdetached from the at least one other aircraft component of the pluralityof aircraft components during the removing.
 20. A method for assemblinga containerized aircraft as a complete aircraft, the method comprising:removing a plurality of aircraft components supported on one or moreshipping fixtures from one or more shipping containers, wherein theplurality of aircraft components comprises a fuselage assembly, one ormore wings, one or more engine assemblies, a vertical tailfin assembly,and a horizontal stabilizer assembly; removing tooling from the one ormore shipping containers, wherein the tooling comprises a plurality ofaircraft component positioning structures, and wherein the plurality ofaircraft component positioning structures comprises a fuselagepositioning structure, one or more wing positioning structures, one ormore engine positioning structures, and an empennage positioningstructure; unloading each aircraft component of the plurality ofaircraft components from the one or more shipping fixtures; indexing theone or more wing positioning structures to the fuselage positioningstructure proximate to lateral portions of the fuselage assembly;loading the one or more wings onto the one or more wing positioningstructures; positioning the one or more wings in one or morecorresponding wing installation positions using the one or more wingpositioning structures; attaching the one or more wings to the fuselageassembly; indexing the empennage positioning structure to the fuselagepositioning structure proximate to an aft region of the fuselageassembly; loading the vertical tailfin assembly onto the empennagepositioning structure; attaching the horizontal stabilizer assembly tothe vertical tailfin assembly on the empennage positioning structure toform an empennage assembly; positioning the empennage assembly in acorresponding empennage installation position using the empennagepositioning structure; attaching the empennage assembly to the fuselageassembly; indexing the one or more engine positioning structures to thefuselage positioning structure proximate to one or more lateral portionsof fuselage assembly beneath the one or more wings; loading the one ormore engine assemblies onto the one or more engine positioningstructures; positioning the one or more engine assemblies in one or morecorresponding engine assembly installation positions using the one ormore engine positioning structures; and attaching the one or more engineassemblies to the one or more wings.